System and method for dynamic excitation of an energy storage element configured for use in an electric aircraft

ABSTRACT

A system for dynamic excitation of an energy storage element configured for use in an electric aircraft includes a plurality of propulsors mechanically connected to the electric aircraft. The system includes a plurality of energy storage elements electrically connected to the plurality of propulsors. The system includes a bus element, wherein the bus element is electrically connected to the plurality of energy storage elements and a cross tie element connected to the bus element configured to disconnect a first energy storage element from a second energy storage element. The system includes a modulator unit electrically connected to the bus element configured to modulate a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The system includes at least a sensor configured to detect an energy datum corresponding to the first energy storage element as a function of the modulation.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of Non-provisional application Ser. No. 17/348,240 filed on Jun. 15, 2021 and entitled “SYSTEM AND METHOD FOR DYNAMIC EXCITATION OF AN ENERGY STORAGE ELEMENT CONFIGURED FOR USE IN AN ELECTRIC AIRCRAFT,” the entirety of which is incorporated herein by reference.

FIELD OF THE INVENTION

The present invention generally relates to the field of electric aircraft. In particular, the present invention is directed to a system and method for dynamic excitation of an energy storage element configured for use in an electric aircraft.

BACKGROUND

In electrically propelled vehicles, such as an electric vertical takeoff and landing (eVTOL) aircraft, it is essential to maintain the integrity of the aircraft until safe landing. In some flights, a component of the aircraft may experience a malfunction or failure which will put the aircraft in an unsafe mode which will compromise the safety of the aircraft, passengers and onboard cargo.

SUMMARY OF THE DISCLOSURE

In an aspect, a system for dynamic excitation of an energy storage element configured for use in an electric aircraft includes a plurality of propulsors mechanically connected to the electric aircraft. The system includes a plurality of energy storage elements electrically connected to the plurality of propulsors. The system includes a bus element, wherein the bus element is electrically connected to the plurality of energy storage elements and a cross tie element connected to the bus element and configured to disconnect a first energy storage element from a second energy storage element. The system includes a modulator unit electrically connected to the bus element configured to modulate a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The system includes at least a sensor configured to detect an energy datum corresponding to the first energy storage element as a function of the modulation.

In another aspect, a method for dynamic excitation of an energy storage element configured for use in electric aircraft includes disconnecting, by a cross tie element connected to a bus element, a first energy storage element electrically connected to the bus element from a second energy storage element electrically connected to the bus element. The method includes modulating, by a modulator unit, a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The method includes detecting, by at least a sensor, an energy datum corresponding to the first energy storage elements as a function of the modulation.

These and other aspects and features of non-limiting embodiments of the present invention will become apparent to those skilled in the art upon review of the following description of specific non-limiting embodiments of the invention in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

For the purpose of illustrating the invention, the drawings show aspects of one or more embodiments of the invention. However, it should be understood that the present invention is not limited to the precise arrangements and instrumentalities shown in the drawings, wherein:

FIG. 1 is a block diagram of an exemplary embodiment of a system for dynamic excitation of an energy storage element configured for use in an electric aircraft;

FIG. 2 is an exemplary method of dynamic excitation of an energy storage element configured for use in an electric aircraft;

FIG. 3A is a schematic diagram of an exemplary embodiment of a system for dynamic excitation of an energy storage element configured for use in an electric aircraft;

FIG. 3B is a schematic diagram of an exemplary embodiment of a system for dynamic excitation of an energy storage element configured for use in an electric aircraft;

FIG. 3C are graphs illustrating power capability of two energy storage elements plotted versus depth of discharge for various discharge capabilities.

FIG. 4A is a schematic diagram an exemplary embodiment of a bus element with energy storage elements connected thereto;

FIG. 4B are graphs illustrating mission power demand of various energy storage configurations plotted versus time;

FIG. 5 is an exemplary embodiment of a battery module configured for use in electric aircraft presented in isometric view;

FIG. 6 is a block diagram of an exemplary embodiment of a machine learning module;

FIG. 7 is an illustration of an exemplary embodiment of an electric aircraft;

FIG. 8 is a block diagram of a computing system that can be used to implement any one or more of the methodologies disclosed herein and any one or more portions thereof; and

FIG. 9 is a block diagram of an exemplary embodiment of a flight controller.

The drawings are not necessarily to scale and may be illustrated by phantom lines, diagrammatic representations and fragmentary views. In certain instances, details that are not necessary for an understanding of the embodiments or that render other details difficult to perceive may have been omitted.

DETAILED DESCRIPTION

In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, that the present invention may be practiced without these specific details. As used herein, the word “exemplary” or “illustrative” means “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” or “illustrative” is not necessarily to be construed as preferred or advantageous over other implementations. All of the implementations described below are exemplary implementations provided to enable persons skilled in the art to make or use the embodiments of the disclosure and are not intended to limit the scope of the disclosure, which is defined by the claims. For purposes of description herein, the terms “upper”, “lower”, “left”, “rear”, “right”, “front”, “vertical”, “horizontal”, and derivatives thereof shall relate to the invention as oriented in FIG. 7 . Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description. It is also to be understood that the specific devices and processes illustrated in the attached drawings, and described in the following specification, are simply embodiments of the inventive concepts defined in the appended claims. Hence, specific dimensions and other physical characteristics relating to the embodiments disclosed herein are not to be considered as limiting, unless the claims expressly state otherwise.

With continued reference to FIG. 1 , an exemplary embodiment of a system 100 for dynamic excitation of an energy storage element configured for use in an electric aircraft is presented in block diagram form. System 100 includes a plurality of propulsors 104 mechanically connected to the electric aircraft. One of ordinary skill in the art, upon reviewing the entirety of this disclosure, will appreciate that ways discussed herein of attaching one or more mechanical elements together such as a propulsor and/or actuator to an electric aircraft are only presented as examples and any number of mechanisms and methods may be used for this purpose. Said mechanical connecting may include, as a non-limiting example, rigid coupling (e.g. beam coupling), bellows coupling, bushed pin coupling, constant velocity, split-muff coupling, diaphragm coupling, disc coupling, donut coupling, elastic coupling, flexible coupling, fluid coupling, gear coupling, grid coupling, hirth joints, hydrodynamic coupling, jaw coupling, magnetic coupling, Oldham coupling, sleeve coupling, tapered shaft lock, twin spring coupling, rag joint coupling, universal joints, welding, riveting, bolts and nuts, crimping, screws, nails, glue and epoxies, or any combination thereof. Any component may include a nonconductive component manufactured from or by a process that renders it incapable or unsuitable for conveying electrical through, on, or over it. Plurality of propulsors 104 may include one or more actuators configured to move one or more control surfaces as a function of one or more control inputs. Plurality of propulsors 104 may be consistent with any propulsor and/or actuator as described in this disclosure. Plurality of propulsors 104 may include one or more processors as described in this disclosure above and configured to control propulsors in the event of one or more computing devices become inoperable.

With continued reference to FIG. 1 , system 100 includes a plurality of energy storage elements 108 electrically connected to plurality of propulsors 104. For the purposes of this disclosure, an “energy storage element” is a device configured to store a form of energy usable by a system in the same or another form of energy. Plurality of energy storage elements 108 may include at least a cell, such as a chemoelectrical, photo electric, or fuel cell. Plurality of energy storage elements 108 may include, without limitation, a generator, a photovoltaic device, a fuel cell such as a hydrogen fuel cell, direct methanol fuel cell, and/or solid oxide fuel cell, or an electric energy storage device; electric energy storage device may include without limitation a capacitor, an inductor, an energy storage cell and/or a battery. Plurality of energy storage elements 108 may be capable of providing sufficient electrical power for auxiliary loads, including without limitation lighting, navigation, communications, de-icing, steering or other systems requiring power or energy. Plurality of energy storage elements 108 may be capable of providing sufficient power for controlled descent and landing protocols, including without limitation hovering descent or runway landing. Plurality of energy storage elements may include a device for which power that may be produced per unit of volume and/or mass has been optimized, at the expense of the maximal total specific energy density or power capability, during design. Plurality of energy storage elements 108 may be used, in an embodiment, to provide electrical power to an electric aircraft or drone, such as an electric aircraft vehicle, during moments requiring high rates of power output, including without limitation takeoff, landing, thermal de-icing and situations requiring greater power output for reasons of stability, such as high turbulence situations. Each energy storage element of plurality of energy storage elements 108 may include a battery pack, a battery module, a battery cell, and/or another device configured to store energy in a retrievable form. For the purposes of this disclosure, a “battery pack” is a device configured to store electrical energy in a plurality of smaller portions which may be selectively discharged. For example, and without limitation, plurality of storage elements 108 may include a battery pack including a plurality of battery modules which may be commanded separately to discharge at different rates or separately, altogether.

With continued reference to FIG. 1 , plurality of energy storage elements 108 may become substantially discharged during any in-flight function due to in-flight power consumption and unforeseen power and current draws that may occur during flight; the power and current draws may be imposed by environmental conditions, components of the energy storage elements or other factors which impact the energy source state of charge (SOC) and/or ability to supply power. For the purposes of this disclosure, a “battery module” is an energy storage device made up of smaller individual battery storage devices connected together. For example, a battery module may include a plurality of battery cells wired together in series and/or parallel configured to store electrical energy. For the purposes of this disclosure, a “battery cell” is an energy storage device. For example, and without limitation, a battery cell may include an electrochemical cell configured to store potential electrical energy in the form of a chemical reaction. Any battery module and/or battery cell described in this disclosure may utilize a plurality of forms of energy storage one of ordinary skill in the art would be aware of including but not limited to, electrochemical energy storage. Plurality of energy storage elements 108 may be electrically connected to plurality of propulsors 104. Plurality of energy storage elements 108 may be configured to transmit electrical energy to power one or more of plurality of propulsors 104. Plurality of energy storage elements 108 may be configured to selectively transmit electrical energy to any of the plurality of propulsors 104. For example, and without limitation, a portion of plurality of energy storage elements 108 may be configured to not transmit electrical energy to one of the plurality of propulsors 104 and transmit a certain amount of electrical energy to a second of the plurality of propulsors 104 and simultaneously transmit less than the certain amount of electrical energy to a third of the plurality of propulsors 104. Plurality of energy storage elements 108 may be divided in any number of smaller energy storage devices such as a plurality of battery modules wired together in series and/or in parallel, wherein the plurality of battery modules may include a plurality of battery cells wired together in series and/or in parallel. Plurality of energy storage elements 108 may include pouch cells, cylindrical cells, electrochemical cells, or any other configuration as described in this disclosure, namely with reference to FIG. 5 .

With continued reference to FIG. 1 , system 100 includes a bus element 112, wherein the bus element is electrically connected to plurality of energy storage elements 108. For the purposes of this disclosure, a “bus element” is an electrically conductive pathway connecting at least a component in a system configured to convey electrical energy between components. Bus element 112 may include one or more electrically conductive pathways configured to transfer electrical energy across the pathways to convey electrical energy from one component to one or more other components. Bus element 112 may include, without limitation, one or more metallic strips and/or bars. Bus element 112 may include a ring bus. For the purpose of this disclosure, a “ring bus” is a bus element wherein circuit breakers are connected to form a ring with isolators on both sides of each circuit breaker. Ring bus may include component configured to isolate a fault by tripping two circuit breakers while all other circuits remain in service. Bus element 112 may be disposed in or on a switchgear, panel board, busway enclosure, plurality of energy storage elements 108, any portion of electric aircraft, plurality of propulsors 104, or a combination thereof. Bus element 112 may also be used to connect high voltage equipment at electrical switchyards, and low voltage equipment in plurality of energy storage elements 108. Bus element 112 may be uninsulated; bus element 112 may have sufficient stiffness to be supported in air by insulated pillars. These features allow sufficient cooling of the conductors, and the ability to tap in at various points without creating a new joint. Bus element 112 may include material composition and cross-sectional size configured to conduct electricity where the size and material determine the maximum amount of current that can be safely carried. Bus element 112 may be produced in a plurality of shapes including flat strips, solid bars, rods, or a combination thereof. Bus element 112 may be composed of copper, brass, aluminum as solid or hollow tubes, in embodiments. Bus element 112 may include flexible buses wherein thin conductive layers are sandwiched together; such an arrangement may include a structural frame and/or cabinet configured to provide rigidity to bus element 112. Bus element 112 may include distribution boards configured to split the electrical supply into separate circuits at one location. Busways, or bus ducts, are long busbars with a protective cover. Rather than branching from the main supply at one location, they allow new circuits to branch off anywhere along the route of the busway. Bus element 112 may either be supported on insulators, or else insulation may completely surround it. Busbars are protected from accidental contact either by an enclosure or by design configured to remove it from reach. Bus element 112 may be connected to each other and to electrical apparatus by bolted, clamped, or welded connections. Joints between high-current bus element 112 sections have precisely machined matching surfaces that are silver-plated to reduce the contact resistance.

With continued reference to FIG. 1 , system 100 includes a cross tie element 116. Cross tie element 116 is connected to the bus element. Cross tie element 116 is configured to disconnect a first energy storage element from a second energy storage element. The first and second energy storage elements may be consistent with any energy storage element as described in this disclosure such as any of plurality of energy storage elements 108. For the purposes of this disclosure, a “cross tie element” is a device or protocol configured to disconnect and electrically isolate a portion of elements connected to a bus element from the rest of the elements connected to bus element. Cross tie element 116 may include a mechanical, electromechanical, hydraulic, pneumatic, or other type of device configured to actuate a portion of bus element 112. Cross tie element 116 may include one or more relays connected to an electrical circuit configured to open or close another circuit as a function of the manipulation of a separate electrical circuit. For example, and without limitation, cross tie element 116 may be configured to receive a datum, more than one elements of data, command, signal, or other communication to engage or disengage to disconnect at least a portion of plurality of energy storage elements 108 from the plurality of energy storage elements 108. Cross tie element 116 may include a switch configured to operate in one of two positions, an open and a closed position. Cross tie element 116 may include electrically actuated switches including transistors, bipolar junction transistors (BJT), field-effect transistors (FETs), metal oxide field-effect transistors (MOSFETs), a combination thereof, or other nondisclosed elements alone or in combination. Cross tie element may include a bus tie element joining two or more elements or groups thereof.

Further referring to FIG. 1 , system 100 may include multiple energy storage elements 108, which may be combined and/or detached from one another using one or more cross tie elements 116. For instance, and without limitation, disconnection of a cross tie element 116 may isolate a single energy storage element of plurality of energy storage elements 108 from all other energy storage elements and/or may isolate a first plurality of energy storage elements from a second plurality of energy storage elements. More generally, any number of cross tie elements 116 may operate to divide plurality of energy storage units 108 into various different groups and/or isolate any single energy storage unit one by one or two or more at a time. Where cross tie element 116 separates a first energy storage unit from a second energy storage unit, either of first or second energy storage unit may be part of a plurality of energy storage units that remain interconnected and/or may be isolated from all other energy storage units.

With continued reference to FIG. 1 , system 100 includes a modulator unit 120 electrically connected to bus element 112. For the purposes of this disclosure, a “modulator unit” is a circuit, which may include any combinational and/or sequential logic circuit and which may be implemented, without limitation, as an application-specific integrated circuit (ASIC), FPGA, and/or at least a computing device, and which is configured to generate electrical signals indicating one or more energy outputs of an energy storage element. Modulator unit 120 may be included in a flight controller, as described in further detail below in reference to FIG. 9 . Modulator unit 120 is electrically and communicatively connected to bus element 112. Modulator unit 120 is configured to modulate an electrical command 124 between at least a portion of plurality of energy storage elements 108 or in other words, modulator unit 120 is configured to modulate a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. The first energy storage element may be a portion of plurality of energy storage elements 108. Second energy storage element may be another distinct portion of plurality of energy storage elements 108. For the purposes of this disclosure, “electrical command” is an electrical signal indicating one or more energy outputs from an energy storage element to another component within a system connected thereto. Modulator unit 120 may include a processor consistent with the description of any processor in this disclosure. Computing device may include any computing device as described in this disclosure, including without limitation a microcontroller, microprocessor, digital signal processor (DSP) and/or system on a chip (SoC) as described in this disclosure. Computing device may include, be included in, and/or communicate with a mobile device such as a mobile telephone or smartphone. System 100 may include a single computing device operating independently, or may include two or more computing device operating in concert, in parallel, sequentially or the like; two or more computing devices may be included together in a single computing device or in two or more computing devices. System 100 may interface or communicate with one or more additional devices as described below in further detail via a network interface device. Network interface device may be utilized for connecting system 100 to one or more of a variety of networks, and one or more devices. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. A network may employ a wired and/or a wireless mode of communication. In general, any network topology may be used. Information (e.g., data, software etc.) may be communicated to and/or from a computer and/or a computing device. System 100 may include but is not limited to, for example, a computing device or cluster of computing devices in a first location and a second computing device or cluster of computing devices in a second location. System 100 may include one or more computing devices dedicated to data storage, security, distribution of traffic for load balancing, and the like. System 100 may distribute one or more computing tasks as described below across a plurality of computing devices of computing device, which may operate in parallel, in series, redundantly, or in any other manner used for distribution of tasks or memory between computing devices. System 100 may be implemented using a “shared nothing” architecture in which data is cached at the worker, in an embodiment, this may enable scalability of system 100 and/or computing device.

With continued reference to FIG. 1 , system 100 and any one or more computing devices may be designed and/or configured to perform any method, method step, or sequence of method steps in any embodiment described in this disclosure, in any order and with any degree of repetition. For instance, system 100 may be configured to perform a single step or sequence repeatedly until a desired or commanded outcome is achieved; repetition of a step or a sequence of steps may be performed iteratively and/or recursively using outputs of previous repetitions as inputs to subsequent repetitions, aggregating inputs and/or outputs of repetitions to produce an aggregate result, reduction or decrement of one or more variables such as global variables, and/or division of a larger processing task into a set of iteratively addressed smaller processing tasks. System 100 may perform any step or sequence of steps as described in this disclosure in parallel, such as simultaneously and/or substantially simultaneously performing a step two or more times using two or more parallel threads, processor cores, or the like; division of tasks between parallel threads and/or processes may be performed according to any protocol suitable for division of tasks between iterations. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various ways in which steps, sequences of steps, processing tasks, and/or data may be subdivided, shared, or otherwise dealt with using iteration, recursion, and/or parallel processing.

With continued reference to FIG. 100 , system 100, processors, and/or controllers may be controlled by one or more Proportional-Integral-Derivative (PID) algorithms driven, for instance and without limitation by stick, rudder and/or thrust control lever with analog to digital conversion for fly by wire as described in this disclosure and related applications incorporated in this disclosure by reference. A “PID controller”, for the purposes of this disclosure, is a control loop mechanism employing feedback that calculates an error value as the difference between a desired setpoint and a measured process variable and applies a correction based on proportional, integral, and derivative terms; integral and derivative terms may be generated, respectively, using analog integrators and differentiators constructed with operational amplifiers and/or digital integrators and differentiators, as a non-limiting example. A similar philosophy to attachment of flight control systems to sticks or other manual controls via pushrods and wire may be employed except the conventional surface servos, steppers, or other electromechanical actuator components may be connected to the cockpit inceptors via electrical wires. Fly-by-wire systems may be beneficial when considering the physical size of the aircraft, utility of for fly by wire for quad lift control and may be used for remote and autonomous use, consistent with the entirety of this disclosure. System 100 may harmonize vehicle flight dynamics with best handling qualities utilizing the minimum amount of complexity whether it be additional modes, augmentation, or external sensors as described in this disclosure.

With continued reference to FIG. 1 , modulator unit 120 may be configured to transmit one or more electrical signals consistent with any description of electrical signals in this disclosure. Modulator unit 120 may be configured to transmit commands to one or more of the plurality of energy storage elements 108 in order to dynamically excite the commanded one or more of the plurality of energy storage elements 108. For the purpose of this disclosure, “dynamic excitation” is commanding of an energy storage element to discharge energy at one or more rates of discharge or total energy discharged. Modulator unit 120 may generate and transmit electrical command 124 to only the portion of the plurality of energy storage elements 120. Modulator unit 120 may generate one or more electrical commands 124 and transmit different electrical commands 124 to separate portions of the plurality of energy storage elements 108. For example, and without limitation, modulator unit 124 may generate and transmit electrical command 124 to the disconnected portion of plurality of energy storage elements 108 and command said portion to discharge a certain amount of energy to power a portion of plurality of propulsors 104.

With continued reference to FIG. 1 , modulator unit 120 may modulate one or more electrical commands 124 to plurality of energy storage elements 108 in order to measure one or more electrical parameters or a change thereof. measuring at least an electrical parameter may include detecting a change in the at least an electrical parameter. In an embodiment, the change in voltage as a function of time may be measured. In an embodiment, a change in current as a function of time may be measured. As an example and without limitation, detecting a change in the at least an electrical parameter may be accomplished by repeatedly measuring or sampling data detected by at least a sensor 128. As another non-limiting example, detecting a change in the at least an electrical parameter may be accomplished by controller, modulator unit 120 or another component using the repeated samples or measurement to calculate changes or rates of change. As a further example and without limitation, detecting a change in the at least an electrical parameter may be accomplished by a curve, graph, or continuum of measured values may be matched to mathematical functions using, such as linear approximation, splining, Fourier series calculations, or the like. In an embodiment, detecting a change in at least an electrical parameter may include, without limitation, detecting a change in a first electrical parameter of the at least an electrical parameter, detecting a change in a second electrical parameter of the at least an electrical parameter, and calculating a dependency of the second electrical parameter on the first electrical parameter. In an embodiment, detecting a change in at least an electrical parameter may further include, without limitation, calculating a change in voltage as a function of time. As an example and without limitation, calculating a change in voltage as a function of time may include sampling voltage repeatedly or continuously over a time period, and the rate of change over time may be observed. As another non-limiting example, detecting a change in at least an electrical parameter may further include, without limitation, detecting current as a function of voltage. As an example and without limitation, detecting current as a function of voltage may include instantaneous or average voltage may be divided by current according to Ohm's law to determine resistance, while instantaneous or average impedance may similarly be calculated using formulas relating voltage, current, or other parameters to impedance. As another non-limiting example, detection of at least an electrical parameter may be performed by digital sampling. As an example and without limitation, digital sampling may include at least an electrical parameter that is directly measured may be sampled, such as, at a rate expressed in frequency of sample per second, such as without limitation a 10 Hz sample rate. Directly measured or sampled electrical parameter may be subjected to one or more signal processing actions, including scaling, low-pass filtering, high-pass filtering, band-pass filtering, band-stop filtering, noise filtering, or the like.

With continued reference to FIG. 1 , modulator unit 120 may modulator electrical command 124 thereby inducing change in first electrical parameter may further include modifying electrical power being supplied to at least a propulsor of the electronic aircraft from an energy source of the at least an energy source. In an embodiment, modulator unit may reduce power to a propulsor from plurality of energy storage elements 108 to reduce speed or altitude. Alternatively or additionally, modulator unit 120 may increase power to a propulsor from plurality of energy storage elements 108, increasing speed or altitude. In an embodiment, when power to propulsor is increased or decreased relatively briefly, or to a limited extent, there may be a negligible change in speed or altitude as a result of the change. Alternatively or additionally, increases or decreases in power to a propulsor may be balanced by counteracting increases or decreases in power. For instance, modulator unit 120 may apply more torque, causing the provision of more power, to one propulsor of multiple propulsors while applying less torque, and thus providing less power to another propulsor, such that net increased or decreased power from all propulsors is unchanged; this may be done alternately between sides so a course of electronic aircraft is unaltered. Alternatively or additionally, plurality of energy storage elements 108 may be connected to a motor that has dual (or multiple) windings, each winding going to a different separate energy source. Power to one set of windings may be increased while power to other windings is deceased, such that at least one of plurality of energy storage elements 108, has a net increase or decrease in power output while a change in propulsive power from the propulsor is negligible or nonexistent. Multiple energy storage elements of plurality of energy storage elements 108, may have power increased or decreased, permitting measurement of resulting changes in at least an electrical parameter for each of multiple energy sources. Modulator unit 120 may include modulating one or more electrical signals consistent with U.S. patent application Ser. No. 16/598,307 titled “METHODS AND SYSTEMS FOR ALTERING POWER DURING FLIGHT” filed on Oct. 10, 2019, which is incorporated herein by reference in its entirety.

With continued reference to FIG. 1 , system 100 includes at least a sensor 128 configured to detect an energy datum 132 corresponding to the first energy storage element as a function of the modulation. At least a sensor 128 may be configured to detect energy datum 132 corresponding to the at least a portion of energy storage elements as a function of the modulation. For the purposes of this disclosure, “energy datum” is at least an element of data representative of one or more characteristics corresponding to at least a portion of the plurality of energy storage elements. Energy datum 132 may include at least an electrical parameter which may include, without limitation, voltage, current, impedance, resistance, and/or temperature. Current may be measured by using a sense resistor in series with the circuit and measuring the voltage drop across the resister, or any other suitable instrumentation and/or methods for detection and/or measurement of current. Voltage may be measured using any suitable instrumentation or method for measurement of voltage, including methods for estimation as described in further detail below. Each of resistance, current, and voltage may alternatively or additionally be calculated using one or more relations between impedance and/or resistance, voltage, and current, for instantaneous, steady-state, variable, periodic, or other functions of voltage, current, resistance, and/or impedance, including without limitation Ohm's law and various other functions relating impedance, resistance, voltage, and current with regard to capacitance, inductance, and other circuit properties.

With continued reference to FIG. 1 , at least a sensor 128 may include at least an environmental sensor. As used in this disclosure, at least an environmental sensor may be used to detect ambient temperature, barometric pressure, air velocity, motion sensors which may include gyroscopes, accelerometers, inertial measurement unit (IMU), various magnetic, humidity, oxygen. At least a sensor 128 may include at least a geospatial sensor. As used in this disclosure, a geospatial sensor may include optical/radar/Lidar, GPS and may be used to detect aircraft location, aircraft speed, aircraft altitude and whether the aircraft is on the correct location of the flight plan. At least a sensor 128 may be located inside the electric aircraft; at least a sensor may be inside a component of the aircraft. In an embodiment, environmental sensor may sense one or more environmental conditions or parameters outside the electric aircraft, inside the electric aircraft, or within or at any component thereof, including without limitation plurality of energy storage elements 108, plurality of propulsors 104, or the like. At least a sensor 128 may be incorporated into vehicle or aircraft or be remote. At least a sensor 128 may include one or more sensors configured to detect electrical phenomena, physical phenomena, or a combination thereof. One of ordinary skill in the art, after reviewing the entirety of this disclosure, will be aware of multiple types, implementations, and uses for a proximity sensor including measuring the distance to a sensor from an object, measuring the rate of change of distance of an object from a sensor, or triggering one or more other circuits as a function of a detection from said proximity circuit, among a plurality of others. At least a sensor 128 may be disposed in, at, or on plurality of storage elements 108. At least a sensor 128 may be mechanically and communicatively connected consistent with the entirety of this disclosure to one or more of plurality of energy storage elements 108.

Still referring to FIG. 1 , at least a sensor 128 may include more than one proximity sensor configured to detect a distance, change in distance, threshold distance, or a combination thereof of one or more components integral to plurality of energy storage elements 108. Proximity sensor may be a sensor able to detect the presence of nearby objects without any physical contact. Proximity sensor may emit an electromagnetic field or a beam of electromagnetic radiation such as infrared, for instance, and looks for changes in the field or a return signal. The object, or portion of plurality of energy storage elements 108 being sensed may be referred to as the proximity sensor's target. Different proximity sensor targets demand different sensors. For example, a capacitive proximity sensor or photoelectric sensor might be suitable for a plastic target; an inductive proximity sensor always requires a metal target. Proximity sensor may include a capacitive proximity sensor, a capacitive proximity sensor may be based on capacitive coupling, that can detect and measure anything that is conductive or has a dielectric different from air.

With continued reference to FIG. 1 ; proximity sensor may include projected capacitive touch (PCT) technology, which is a capacitive technology which allows more accurate and flexible operation, by etching the conductive layer. A grid may be formed either by etching one layer to form a grid pattern of electrodes, or by etching two separate, parallel layers of conductive material with perpendicular lines or tracks to form the grid; comparable to the pixel grid found in many liquid crystal displays (LCD). The greater resolution of PCT allows operation with no direct contact, such that the conducting layers can be coated with further protective insulating layers, and operate even under screen protectors, or behind weather and vandal-proof glass. Because a top layer of a PCT may be composed of glass, PCT may represent a more robust solution versus resistive touch technology. PCT may include a self-capacitance and/or mutual capacitance. For the purposes of this disclosure, “mutual capacitive” sensors have a capacitor at each intersection of each row and each column. Proximity sensor may also be used to detect machine vibration monitoring to measure the variation in distance between a shaft and its support bearing or any two or more elements included by plurality of energy storage elements 108. Proximity sensor may include a photoelectric sensor. A photoelectric sensor may be a device used to determine the distance, absence, or presence of an object by using a light transmitter, often infrared and a photoelectric receiver.

With continued reference to FIG. 1 , proximity sensor may include opposed (through-beam), retro-reflective, and proximity-sensing (diffused) types of proximity sensors. A through-beam arrangement may consist of a receiver located within the line-of-sight of the transmitter. In this mode, an object may be detected when the light beam is blocked from getting to the receiver from the transmitter. A retroreflective arrangement may place the transmitter and receiver at the same location and uses a reflector to bounce the inverted light beam back from the transmitter to the receiver. An object may be sensed when the beam is interrupted and fails to reach the receiver. A proximity-sensing (diffused) arrangement may be one in which the transmitted radiation must reflect off the object in order to reach the receiver. In this mode, an object is detected when the receiver sees the transmitted source rather than when it fails to see it. As in retro-reflective sensors, diffuse sensor emitters and receivers may be located in the same housing. But the target acts as the reflector so that detection of light is reflected off the disturbance object. The emitter may send out a beam of light (most often a pulsed infrared, visible red, or laser) that diffuses in all directions, filling a detection area. The target may then enter the area and deflects part of the beam back to the receiver. Detection occurs and output is turned on or off when sufficient light falls on the receiver. Some photo-eyes have two different operational types, light operate and dark operate. The light operates photo eyes become operational when the receiver “receives” the transmitter signal. Dark operate photo eyes become operational when the receiver “does not receive” the transmitter signal. The detecting range of a photoelectric sensor may be its “field of view”, or the maximum distance from which the sensor can retrieve information, minus the minimum distance. A minimum detectable object is the smallest object the sensor can detect.

With continued reference to FIG. 1 , proximity sensor may include an electromagnetic induction sensor configured to use the principle of electromagnetic induction to detect or measure objects. An inductor develops a magnetic field when a current flows through it; alternatively, a current will flow through a circuit containing an inductor when the magnetic field through it changes. This effect can be used to detect metallic objects that interact with a magnetic field. Nonmetallic substances such as liquids or some kinds of dirt do not interact with the magnetic field, so an inductive sensor can operate in wet or dirty conditions which may arise in or on plurality of energy storage elements 108.

With continued reference to FIG. 1 , at least a sensor 128 may include a load cell. A load cell may be a force transducer. It may convert a force such as tension, compression, pressure, or torque into an electrical signal that can be measured and standardized. At least a sensor 128 may, in a load cell embodiment measure the force of one or more expanding or contracting elements included by plurality of energy storage elements 108. As the force applied to the load cell increases, the electrical signal changes proportionally. Load cell may be strain gauges, pneumatic, and hydraulic, and in non-limiting embodiments, at least a sensor 128 may include these or other nondisclosed sensors alone or in combination.

Referring now to FIG. 1 , at least a sensor 128 may include a plurality of sensors in the form of individual sensors or a sensor suite working in tandem or individually. A sensor suite may include a plurality of independent sensors, as described in this disclosure, where any number of the described sensors may be used to detect any number of physical or electrical quantities associated with an aircraft power system or an electrical energy storage system. Independent sensors may include separate sensors measuring physical or electrical quantities that may be powered by and/or in communication with circuits independently, where each may signal sensor output to a control circuit such as a user graphical interface. In a non-limiting example, there may be four independent sensors housed in and/or on battery module 500 measuring temperature, electrical characteristic such as voltage, amperage, resistance, or impedance, proximity, or any other parameters and/or quantities as described in this disclosure. In an embodiment, use of a plurality of independent sensors may result in redundancy configured to employ more than one sensor that measures the same phenomenon, those sensors being of the same type, a combination of, or another type of sensor not disclosed, so that in the event one sensor fails, the ability of system 100 and/or user to detect phenomenon is maintained and in a non-limiting example, a user alter aircraft usage pursuant to sensor readings.

With continued reference to FIG. 1 , at least a sensor 128 may include electrical sensors. Electrical sensors may be configured to measure voltage across a component, electrical current through a component, and resistance of a component. Electrical sensors may include separate sensors to measure each of the previously disclosed electrical characteristics such as voltmeter, ammeter, and ohmmeter, respectively.

With continued reference to FIG. 1 , alternatively or additionally, at least a sensor 128 may include a sensor or plurality thereof configured to detect voltage and direct the charging of individual energy storage elements such as battery cells according to charge level; detection may be performed using any suitable component, set of components, and/or mechanism for direct or indirect measurement and/or detection of voltage levels, including without limitation comparators, analog to digital converters, any form of voltmeter, or the like. At least a sensor 128 and/or a control circuit incorporated therein and/or communicatively connected thereto may be configured to adjust charge to one or more the battery cells as a function of a charge level and/or a detected parameter. For instance, and without limitation, at least a sensor 128 may be configured to determine that a charge level of a battery cell is high based on a detected voltage level of that battery cell or portion of the battery pack. At least a sensor 128 may alternatively or additionally detect a charge reduction event, defined for purposes of this disclosure as any temporary or permanent state of a battery cell requiring reduction or cessation of charging; a charge reduction event may include a cell being fully charged and/or a cell undergoing a physical and/or electrical process that makes continued charging at a current voltage and/or current level inadvisable due to a risk that the cell will be damaged, will overheat, or the like. Detection of a charge reduction event may include detection of a temperature, of the cell above a threshold level, detection of a voltage and/or resistance level above or below a threshold, or the like. At least a sensor 128 may include digital sensors, analog sensors, or a combination thereof. At least a sensor 128 may include digital-to-analog converters (DAC), analog-to-digital converters (ADC, A/D, A-to-D), a combination thereof, or other signal conditioning components used in transmission of a first plurality of battery pack data to a destination over wireless or wired connection.

With continued reference to FIG. 1 , at least a sensor 128 may include thermocouples, thermistors, thermometers, passive infrared sensors, resistance temperature sensors (RTD's), semiconductor based integrated circuits (IC), a combination thereof or another undisclosed sensor type, alone or in combination. Temperature, for the purposes of this disclosure, and as would be appreciated by someone of ordinary skill in the art, is a measure of the heat energy of a system. Temperature, as measured by any number or combinations of sensors present within at least a sensor 128, may be measured in Fahrenheit (° F.), Celsius (° C.), Kelvin (° K), or another scale alone or in combination. The temperature measured by sensors may include electrical signals which are transmitted to their appropriate destination wireless or through a wired connection.

With continued reference to FIG. 1 , at least a sensor 128 may include a sensor configured to detect gas that may be emitted during or after a cell failure. “Cell failure”, for the purposes of this disclosure, refers to a malfunction of a battery cell, which may be an electrochemical cell, that renders the cell inoperable for its designed function, namely providing electrical energy to at least a portion of an electric aircraft. Byproducts of cell failure may include gaseous discharge including oxygen, hydrogen, carbon dioxide, methane, carbon monoxide, a combination thereof, or another undisclosed gas, alone or in combination. Further the sensor configured to detect vent gas from electrochemical cells may include a gas detector. For the purposes of this disclosure, a “gas detector” is a device used to detect a gas is present in an area. Gas detectors, and more specifically, the gas sensor that may be used in at least a sensor 128, may be configured to detect combustible, flammable, toxic, oxygen depleted, a combination thereof, or another type of gas alone or in combination. The gas sensor that may be present in at least a sensor 128 may include a combustible gas, photoionization detectors, electrochemical gas sensors, ultrasonic sensors, metal-oxide-semiconductor (MOS) sensors, infrared imaging sensors, a combination thereof, or another undisclosed type of gas sensor alone or in combination. At least a sensor 128 may include sensors that are configured to detect non-gaseous byproducts of cell failure including, in non-limiting examples, liquid chemical leaks including aqueous alkaline solution, ionomer, molten phosphoric acid, liquid electrolytes with redox shuttle and ionomer, and salt water, among others. At least a sensor 128 may include sensors that are configured to detect non-gaseous byproducts of cell failure including, in non-limiting examples, electrical anomalies as detected by any of the previous disclosed sensors or components.

With continued reference to FIG. 1 , at least a sensor 128 may be configured to detect events where voltage nears an upper voltage threshold or lower voltage threshold. The upper voltage threshold may be stored in data storage system for comparison with an instant measurement taken by any combination of sensors present within at least a sensor 128. The upper voltage threshold may be calculated and calibrated based on factors relating to battery cell health, maintenance history, location within battery pack, designed application, and type, among others. At least a sensor 128 may measure voltage at an instant, over a period of time, or periodically. At least a sensor 128 may be configured to operate at any of these detection modes, switch between modes, or simultaneous measure in more than one mode. First battery management component may detect through at least a sensor 128 events where voltage nears the lower voltage threshold. The lower voltage threshold may indicate power loss to or from an individual battery cell or portion of the battery pack. First battery management component may detect through at least a sensor 128 events where voltage exceeds the upper and lower voltage threshold. Events where voltage exceeds the upper and lower voltage threshold may indicate battery cell failure or electrical anomalies that could lead to potentially dangerous situations for aircraft and personnel that may be present in or near its operation.

With continued reference to FIG. 1 , one or more sensors including at least a sensor 128 may be communicatively connected to at least a pilot control, the manipulation of which, may constitute at least an aircraft command. “Communicative connecting”, for the purposes of this disclosure, refers to two or more components electrically, or otherwise connected and configured to transmit and receive signals from one another. Signals may include electrical, electromagnetic, visual, audio, radio waves, or another undisclosed signal type alone or in combination. Any datum or signal in this disclosure may include an electrical signal. Electrical signals may include analog signals, digital signals, periodic or aperiodic signal, step signals, unit impulse signal, unit ramp signal, unit parabolic signal, signum function, exponential signal, rectangular signal, triangular signal, sinusoidal signal, sinc function, or pulse width modulated signal. At least a sensor may include circuitry, computing devices, electronic components or a combination thereof that translates input datum into at least an electronic signal configured to be transmitted to another electronic component. At least a sensor communicatively connected to at least a pilot control may include a sensor disposed on, near, around or within at least pilot control. At least a sensor may include a motion sensor. “Motion sensor”, for the purposes of this disclosure refers to a device or component configured to detect physical movement of an object or grouping of objects. One of ordinary skill in the art would appreciate, after reviewing the entirety of this disclosure, that motion may include a plurality of types including but not limited to: spinning, rotating, oscillating, gyrating, jumping, sliding, reciprocating, or the like. At least a sensor may include, torque sensor, gyroscope, accelerometer, torque sensor, magnetometer, inertial measurement unit (IMU), pressure sensor, force sensor, proximity sensor, displacement sensor, vibration sensor, among others. At least a sensor may include a sensor suite which may include a plurality of sensors that may detect similar or unique phenomena. For example, in a non-limiting embodiment, sensor suite may include a plurality of accelerometers, a mixture of accelerometers and gyroscopes, or a mixture of an accelerometer, gyroscope, and torque sensor.

With continued reference to FIG. 1 , any of the sensors described in this disclosure may be included within a sense board, wherein the sense board may include sensors configured to measure physical and/or electrical parameters, such as without limitation temperature and/or voltage, of one or more the battery cells. Sense board and/or a control circuit incorporated therein and/or communicatively connected thereto, may further be configured to detect failure within each battery cell, for instance and without limitation as a function of and/or using detected physical and/or electrical parameters. Cell failure may be characterized by a spike in temperature and sense board may be configured to detect that increase and generate signals, which are discussed further below, to notify users, support personnel, safety personnel, maintainers, operators, emergency personnel, aircraft computers, or a combination thereof. Sense board may include thermocouples, thermistors, thermometers, passive infrared sensors, resistance temperature sensors (RTD's), semiconductor based integrated circuits (IC), a combination thereof or another undisclosed sensor type, alone or in combination. Temperature, for the purposes of this disclosure, and as would be appreciated by someone of ordinary skill in the art, is a measure of the heat energy of a system. Heat energy is, at its core, the measure of kinetic energy of matter present within a system. Temperature, as measured by any number or combinations of sensors present on a sense board, may be measured in Fahrenheit (° F.), Celsius (° C.), Kelvin (° K), or another scale alone or in combination. The temperature measured by sensors may include electrical signals which are transmitted to their appropriate destination wireless or through a wired connection.

Further referring to FIG. 1 , a sense board may detect voltage and direct the charging or discharging of individual the battery cells according to charge level; detection may be performed using any suitable component, set of components, and/or mechanism for direct or indirect measurement and/or detection of voltage levels, including without limitation comparators, analog to digital converters, any form of voltmeter, or the like.

Further referring to FIG. 1 , system 100 may include one or more computing devices such as a sense board and/or a control circuit incorporated therein and/or communicatively connected thereto may be configured to adjust charge to at least one battery cell of the plurality of the battery cells as a function of the detected parameter; this may include adjustment in charge as a function of detection of a charge reduction event. Alternatively, or additionally, sense board and/or a control circuit incorporated therein and/or communicatively connected thereto may be configured to increase charge to a cell upon detection that a charge reduction event has ceased; for instance, sense board and/or a control circuit incorporated therein and/or communicatively connected thereto may detect that a temperature of a subject battery cell has dropped below a threshold and may increase charge again. Charge may be regulate using any suitable means for regulation of voltage and/or current, including without limitation use of a voltage and/or current regulating component, including one that may be electrically controlled such as a transistor; transistors may include without limitation bipolar junction transistors (BJTs), field effect transistors (FETs), metal oxide field semiconductor field effect transistors (MOSFETs), and/or any other suitable transistor or similar semiconductor element. Voltage and/or current to one or more cells may alternatively or additionally be controlled by thermistor in parallel with a cell that reduces its resistance when a temperature of the cell increases, causing voltage across the cell to drop, and/or by a current shunt or other device that dissipates electrical power, for instance through a resistor.

Still referring to FIG. 1 , system 100 may include a high current busbar and integral electrical connections. System 100 may charge individual the battery cells depending on battery cell charge levels. Charging may be balanced throughout the plurality of the battery cells by directing energy through balance resistors by dissipating current through resistors as heat. In this manner, the battery cells may be charged evenly, for example, cells with a lower amount of electrical energy will charge more than the battery cells with a greater amount of energy. Cell charge balancing may be controlled via any means described above for regulation of charge levels, including without limitation metal oxide silicon field effect transistor or a metal oxide semiconductor field effect transistor (MOSFET).

With continued reference to FIG. 1 , outputs from any sensors or any other component present within system may be analog or digital. Onboard or remotely located processors can convert those output signals from the sensor suite to a usable form by the destination of those signals. The usable form of output signals from sensors, through processor may be either digital, analog, a combination thereof or an otherwise unstated form. Processing may be configured to trim, offset, or otherwise compensate the outputs of sensor suite. Based on sensor output, the processor can determine the output to send to downstream component. Processor can include signal amplification, operational amplifier (OpAmp), filter, digital/analog conversion, linearization circuit, current-voltage change circuits, resistance change circuits such as Wheatstone Bridge, an error compensator circuit, a combination thereof or otherwise undisclosed components. Any signal as described in this disclosure may be manipulated by one or more computing devices or components thereof. An integrator may include an operational amplifier configured to perform a mathematical operation of integration of a signal; output voltage may be proportional to input voltage integrated over time. An input current may be offset by a negative feedback current flowing in the capacitor, which may be generated by an increase in output voltage of the amplifier. The output voltage may be therefore dependent on the value of input current it has to offset and the inverse of the value of the feedback capacitor. The greater the capacitor value, the less output voltage has to be generated to produce a particular feedback current flow. The input impedance of the circuit may be almost zero because of the Miller effect. Hence all the stray capacitances (the cable capacitance, the amplifier input capacitance, etc.) are virtually grounded and they have no influence on the output signal. An operational amplifier as used in an integrator may be used as part of a positive or negative feedback amplifier or as an adder or subtractor type circuit using just pure resistances in both the input and the feedback loop. As its name implies, the Op-amp Integrator is an operational amplifier circuit that causes the output to respond to changes in the input voltage over time as the op-amp produces an output voltage which may be proportional to the integral of the input voltage. In other words, the magnitude of the output signal may be determined by the length of time a voltage may be present at its input as the current through the feedback loop charges or discharges the capacitor as the required negative feedback occurs through the capacitor. Input voltage may be Vin and represent the input signal to processor such as one or more of input datum and/or attitude error. Output voltage Vout may represent output voltage such as one or more outputs like rate setpoint. When a step voltage, Vin may be firstly applied to the input of an integrating amplifier, the uncharged capacitor C has very little resistance and acts a bit like a short circuit allowing maximum current to flow via the input resistor, Rin as potential difference exists between the two plates. No current flows into the amplifiers input and point X may be a virtual earth resulting in zero output. As the impedance of the capacitor at this point may be very low, the gain ratio of X_(C)/R_(IN) may be also very small giving an overall voltage gain of less than one, (voltage follower circuit). As the feedback capacitor, C begins to charge up due to the influence of the input voltage, its impedance Xc slowly increase in proportion to its rate of charge. The capacitor charges up at a rate determined by the RC time constant, (τ) of the series RC network. Negative feedback forces the op-amp to produce an output voltage that maintains a virtual earth at the op-amp's inverting input. Since the capacitor may be connected between the op-amp's inverting input (which may be at virtual ground potential) and the op-amp's output (which may be now negative), the potential voltage, Vc developed across the capacitor slowly increases causing the charging current to decrease as the impedance of the capacitor increases. This results in the ratio of Xc/Rin increasing producing a linearly increasing ramp output voltage that continues to increase until the capacitor may be fully charged. At this point the capacitor acts as an open circuit, blocking any more flow of DC current. The ratio of feedback capacitor to input resistor (X_(C)/R_(IN)) may be now infinite resulting in infinite gain. The result of this high gain, similar to the op-amps open-loop gain, may be that the output of the amplifier goes into saturation as shown below. (Saturation occurs when the output voltage of the amplifier swings heavily to one voltage supply rail or the other with little or no control in between). The rate at which the output voltage increases (the rate of change) may be determined by the value of the resistor and the capacitor, “RC time constant”. By changing this RC time constant value, either by changing the value of the Capacitor, C or the Resistor, R, the time in which it takes the output voltage to reach saturation can also be changed for example.

With continued reference to FIG. 1 , energy datum 132 may include at least an element of data representative of one or more characteristics of at least a portion of plurality of energy storage elements 108. For example, and without limitation, a portion of the plurality of energy storage elements 108 may have been commanded by modulator unit 120 to discharge energy, at least a sensor 128 may then detect energy datum 132 as a function of that discharging associated with the portion of plurality of energy storage elements 132. Energy datum 132 may include a charge datum. For the purposes of this disclosure, a “charge datum” is one or more elements of data related to at least a portion of plurality of energy storage element's 108 state of charge (SoC). For the purposes of this disclosure, “state of charge” is the level of charge of an electric battery relative to its capacity. The units of SoC may be percentage points (0%=empty; 100%=full). An alternative form of the same measure is the depth of discharge (DoD), the inverse of SoC (100%=empty; 0%=full). SoC is normally used when discussing the current state of a battery in use, while DoD is may be often seen when discussing the lifetime of the battery after repeated use. Charge datum may be one or more elements of data related to the charge of a battery configured for use in an electric aircraft. In an EVTOL, for example, SoC for the plurality of energy storage elements 108 may be the equivalent of a fuel gauge in a gasoline powered vehicle. Charge datum may be calculated, adjusted, searched for in a table, retrieved from a database based on one or more detected parameters, or directly detected, among others. In embodiments, the charge datum may be compared to a calculated charge datum. For the purposes of this disclosure, a “calculated charge datum” is one or more elements of data representing the predicted state of charge of at least a portion of an energy storage device, calculated by a computing device as a function of time.

With continued reference to FIG. 1 , energy datum 132 may include a health datum. Processor may be configured to generate health datum as a function of status datum corresponding to the at least a portion of plurality of energy storage elements 108. For the purposes of this disclosure, a “health datum” includes one or more elements of data related to the state of health (SoH) of plurality of energy storage elements 108. For the purposes of this disclosure, “state of health” is a figure of merit of the condition of a battery (or a cell, or a battery pack), compared to its ideal conditions. The units of SoH are percent points (100%=the battery's conditions match the battery's specifications). Typically, a battery's SoH will be 100% at the time of manufacture and will decrease over time and use. However, a battery's performance at the time of manufacture may not meet its specifications, in which case its initial SoH will be less than 100%. In exemplary embodiments, one or more elements of system 100 including but not limited to processor 120 may evaluate state of health of the portion of battery corresponding to health datum. Health datum may be compared to a threshold health datum corresponding to the parameter detected to generate said health datum. Health datum may be utilized to determine, by processor, the suitability of plurality of energy storage elements 108 to a given application, such as aircraft flight envelope, mission, cargo capacity, speed, maneuvers, or the like.

With continued reference to FIG. 1 , health datum may include a useful life estimate corresponding to plurality of energy storage elements 108. For the purposes of this disclosure, a “useful life estimate” is one or more elements of data indicating a remaining usability of one or more elements of an energy storage device, wherein the usability is a function of whether or not the one or more energy storage elements may be used in performing their designed functions. Useful life estimate may include one or more elements of data related to the remaining use of plurality of energy storage elements 108. Useful life estimate may include a time limit, usage limit, amperage per time parameter, electric parameter, internal resistance, impedance, conductance, capacity, voltage, self-discharge, ability to accept a charge, number of charge-discharge cycles, age of battery, temperature of battery during previous uses, current or future temperature limitations, total energy charged, total energy discharge, or predictions of failures corresponding to plurality of energy storage elements 108. Processor may be configured to select a datum of a plurality of data and utilize the datum to determine charge datum and health datum. Processor may select data collected from one or more sensors described in this disclosure or one or more elements of data input to a system from which processor may retrieve. Processor may be communicatively connected to one or more databases, datastores, lists, matrices, and/or groups that represent and organize data associated with plurality of energy storage elements 108. Processor is configured to transmit the charge datum and health datum to one or more other elements included by system 100 configured to receive one or more elements of data.

With continued reference to FIG. 1 , system 100 may include energy datum 132, wherein energy datum 132 may include a performance characteristic. For the purposes of this disclosure, a “performance characteristic” is at least an element of data representative of performance related to at least a portion of an electric aircraft and/or subsystem thereof. For example, and without limitation, performance characteristic may include a measure of efficiency of one or more of plurality of propulsors 104, plurality of energy storage elements 108, any one or more of the components thereof, or another subsystem of electric aircraft. Performance characteristic may include a measure of temperature of one or more components described in this disclosure. Performance characteristic may include a measure of conductivity, impedance, resistivity, capacitance, current, voltage, or another electrical characteristic of plurality of energy storage elements 108. Performance characteristic may include a measure of a predicted value compared to a measured value.

With continued reference to FIG. 1 , system 100 may include energy datum 132 which may be utilized to generate at least a performance datum. For the purposes of this disclosure, “performance datum” is at least an element of data representative of the performance of at least a portion of plurality of energy storage elements generated as a function of at least a measured value. For example, and without limitation, performance datum may include a measured level of charge of at least a portion of plurality of energy storage elements 108 compared to a calculated or predicted level of charge. In general, and without limitation, predicted values related to the herein disclosed system may be generated by one or more computing devices, one or more processors, input by a user, input by a pilot, generated as a function of one or more previous flights or operations, or a combination thereof. For example, and without limitation, performance datum may include a measured state of health of at least a portion of plurality of energy storage elements 108 compared to a calculated or predicted state of health. In general, and without limitation, predicted values related to the herein disclosed system may be generated by one or more computing devices, one or more processors, input by a user, input by a pilot, generated as a function of one or more previous flights or operations, or a combination thereof. Performance datum may include configurable elements of data input by a user or a pilot. For example, and without limitation, performance datum may be set before a mission, wherein a pilot or user desires to generate performance datum including total current flowed out of a plurality of energy storage elements 108. One of ordinary skill in the art would appreciate, after reviewing the entirety of this disclosure, the near limitless configurations of data that may be generated as a function of energy datum 132.

With continued reference to FIG. 1 , energy datum 132 may be displayed to one or more pilots and or users by display 136. For the purposes of this disclosure, “display” is a device configured to present information to one or more users or computing devices in a perceivable format. Display 136, in nonlimiting embodiments may include audio, visual, tactile, olfactory, or other cues in order to notify a user or computing device of information. In non-limiting examples, display 136 may include a primary flight display (PFD), multi-function display (MFD), heads-up display (HUD), holograph, projection, gauges, audio cues, video cues, data streams, displayed in a pilot's goggles or helmet, and the like. The details of the display layout on a primary flight display can vary enormously, depending on the aircraft, the aircraft's manufacturer, the specific model of PFD, certain settings chosen by the pilot, and various internal options that are selected by the aircraft's owner (i.e., an airline, in the case of a large airliner). However, the great majority of PFDs follow a similar layout convention. The center of the PFD usually contains an attitude indicator (AI), which gives the pilot information about the aircraft's pitch and roll characteristics, and the orientation of the aircraft with respect to the horizon. Unlike a traditional attitude indicator, however, the mechanical gyroscope is not contained within the panel itself but is rather a separate device whose information is simply displayed on the PFD. Attitude indicator is designed to look very much like traditional mechanical AIs. Other information that may or may not appear on or about the attitude indicator can include the stall angle, a runway diagram, ILS localizer and glide-path “needles”, and so on. Unlike mechanical instruments, this information can be dynamically updated as required; the stall angle, for example, can be adjusted in real time to reflect the calculated critical angle of attack of the aircraft in its current configuration (airspeed, etc.). The PFD may also show an indicator of the aircraft's future path (over the next few seconds), as calculated by onboard computers, making it easier for pilots to anticipate aircraft movements and reactions. To the left and right of the attitude indicator are usually the airspeed and altitude indicators, respectively. Airspeed indicator displays the speed of the aircraft in knots, while the altitude indicator displays the aircraft's altitude above mean sea level (AMSL). These measurements are conducted through the aircraft's pitot system, which tracks air pressure measurements. As in the PFD's attitude indicator, these systems are merely displayed data from the underlying mechanical systems, and do not contain any mechanical parts (unlike an aircraft's airspeed indicator and altimeter). Both of these indicators are usually presented as vertical “tapes”, which scroll up and down as altitude and airspeed change. Both indicators may often have “bugs”, that is, indicators that show various important speeds and altitudes, such as V speeds calculated by a flight management system, do-not-exceed speeds for the current configuration, stall speeds, selected altitudes and airspeeds for the autopilot, and so on. At the bottom of the PFD is the heading display, which shows the pilot the magnetic heading of the aircraft. This functions much like a standard magnetic heading indicator, turning as required. Often this part of the display shows not only the current heading, but also the current track (actual path over the ground), rate of turn, current heading setting on the autopilot, and other indicators. Other information displayed on the PFD includes navigational marker information, bugs (to control the autopilot), ILS glideslope indicators, course deviation indicators, altitude indicator QFE settings, and much more. Although the layout of a PFD can be very complex, once a pilot is accustomed to it the PFD can provide an enormous amount of information with a single glance. Any of the herein described PFD layouts or components may display, in whole or in part, energy datum 132, performance datum, performance characteristic, charge datum, and health datum.

With continued reference to FIG. 1 , display 136 may include a multi-function display (MFD). An MFD may be a small-screen surrounded by configurable buttons that can be used to display information to the user in numerous configurable ways. An MFD may be configured to display any one or more elements of data energy datum 132, performance datum, performance characteristic, charge datum, health datum, or a combination thereof, among others. Display 136 may be configured to display useful life estimate corresponding to plurality of energy storage elements 108.

Still referring to FIG. 1 , system 100 may include a first propulsor element 140 and a second propulsor element 144. A “propulsor element,” as used in this disclosure, is an electronic circuit and/or circuit element powering a propulsor. A propulsor element may include, without limitation, a propulsor motor, a winding in a propulsor motor, such as one of a plurality of stator windings, an inverter, an electromagnetic element, or the like. First propulsor element 140 and second propulsor element 144 may be and/or be incorporated in separate motors, and/or may be elements powering the same propulsor; for instance, first propulsor element 140 and second propulsor element 144 may be and/or be connected to two windings on a single propulsor motor. First propulsor element 140 and second propulsor element 144 are incorporated in the plurality of propulsors. In an embodiment, first energy storage unit is electrically connected to first propulsor element 140 and second energy storage element is electrically connected to a second propulsor element. Modulator unit 120 is configured to modulate a first electrical command to the first propulsor element and a second electrical command to the second propulsor element.

Referring now to FIG. 2 , a method 200 for dynamic excitation of an energy storage element configured for use in electric aircraft includes, at 205, disconnecting, by a cross tie element connected to a bus element, a first energy storage element electrically connected to the bus element from a second energy storage element electrically connected to the bus element. Cross tie element may be consistent with any cross tie element as described in this disclosure. Cross tie element may include a switch. Switch may be consistent with any switch as described in this disclosure. The first energy storage element and the second energy storage element may be consistent with any energy storage element as described in this disclosure. At least a portion of the energy storage element may be disconnected from the plurality of the energy storage element by disconnection of the cross tie element. Bus element may be consistent with any bus element as described in this disclosure. The plurality of energy storage element may include a battery module or plurality thereof. Battery module may be consistent with any battery module described in this disclosure.

Still referring to FIG. 200 , at 210, includes modulating, by a modulator unit, a first electrical command to the first energy storage element and a second electrical command to the second energy storage element. Modulator unit may be consistent with any modulator unit as described in this disclosure. First and second electrical commands may be consistent with any electrical command as described in this disclosure. First and second energy storage element may be consistent with any energy storage element as described in this disclosure. Plurality of energy storage elements may be consistent with any plurality of energy storage elements as described in this disclosure. Modulator unit may include a processor. Processor may be consistent with any processor as described in this disclosure. Modulating electrical command between at least a portion of the plurality of energy storage elements may include drawing electrical energy from at least a portion of the plurality of energy storage elements. Electrical energy may be consistent with any electrical energy as described in this disclosure. Modulator may be configured to transmit a command to a propulsor element to modify the power consumed by and/or output through the propulsor element, for instance and without limitation as described above.

Still referring to FIG. 200 , at step 215 at least a sensor detects an energy datum corresponding to the first energy storage element as a function of the modulation. At least a sensor may be consistent with any at least a sensor as described in this disclosure. Energy datum may be consistent with any energy datum as described in this disclosure. First energy storage element may be consistent with any energy storage element as described in this disclosure. Plurality of energy storage elements may be consistent with any plurality of energy storage elements as described in this disclosure. Energy datum may include a charge level corresponding to the plurality of energy storage elements. Charge level may be consistent with any charge level as described in this disclosure. Energy datum may include a performance characteristic of the plurality of energy storage elements. Performance characteristic of the plurality of energy storage elements may be consistent with any performance characteristic as described in this disclosure. Energy datum may be utilized to generate at least a performance datum. Performance datum may be consistent with any performance datum as described in this disclosure. Energy datum may be displayed to a pilot. Displaying to a pilot may include any display as described in this disclosure. Display may be consistent with any display as described in this disclosure.

Referring now to FIG. 3A, a schematic diagram of an exemplary embodiment of system 300 is presented. System 300 includes first energy storage element 304. First energy storage element 304 may be consistent with any energy storage element as described in this disclosure. For example, and without limitation, first energy storage element 304 may include a plurality of battery packs, battery modules, battery cells, or other types of energy storage elements electrically connected together in series and/or parallel. One of ordinary skill in the art would appreciate that there are two energy storage elements illustrated in FIG. 3A, however, any number of energy storage elements may be included in system and operate according to the herein described methodology.

With continued reference to FIG. 3A, exemplary embodiment of system 300 may include bus element 308. Bus element 308 may be consistent with any bus element as described in this disclosure. Bus element 308 may include any manner of conductive material configured to convey electrical energy in any form as described in this disclosure between components. For example, and without limitation, bus element 308 may include any number of components electrically connected thereto, including circuit elements, energy storage elements, propulsors, flight control components, one or more computing devices, sensors, or combination thereof, among others. Bus element 308 may include a plurality of wires and/or conductive strips, bars, structures, or a combination thereof. Bus element 308 may be configured to convey electrical energy configured to power one or more other components electrically connected thereto and/or be configured to convey electrical energy configured to transmit signals between one or more components.

With continued reference to FIG. 3A, exemplary embodiment of system 300 may include a cross tie element 312. Cross tie element 312 may be consistent with any cross tie element as described in this disclosure. Cross tie element 312 may include any electrical switches, relays, components, or combinations thereof. Cross tie element 312 may be electrically connected to bus element 308 and through said bus element 308 may be electrically and communicatively connected to any one or more components as described in this disclosure, namely any of the plurality of energy storage elements such as first energy storage element 304. Cross tie element 312 may be configured to receive one or more electrical signals configured to open or close cross tie element 312. Cross tie element 312, through said opening and closing may electrically disconnect or connect, respectively, first energy storage element from second energy storage element or plurality of energy storage elements as described in this disclosure.

With continued reference to FIG. 3A, exemplary embodiment of system 300 may include a propulsor 316. Propulsor 316 may be electrically and communicatively connected to any of the plurality of other components as described in this disclosure through bus element 308. Propulsor 316 may be one of a plurality of propulsors as described in this disclosure. For example, and without limitation, propulsor 316 may include an electric motor, an actuator consistent with any actuator as described in this disclosure, one or more computing devices, or any other propulsor configured to manipulate a fluid medium.

Referring now to FIG. 3B, a schematic diagram of another exemplary embodiment of system 300 is presented in schematic form. System 300 may include a first energy storage element 304. First energy storage element 304 may be consistent with any energy storage element as described in this disclosure. For example, and without limitation, first energy storage element 304 may include a plurality of battery packs, battery modules, battery cells, or other types of energy storage elements electrically connected together in series and/or parallel. One of ordinary skill in the art would appreciate that there are five energy storage elements illustrated in FIG. 3A, however, any number of energy storage elements may be included in system and operate according to the herein described methodology. For example, and without limitation, first energy storage element 304 and any of the plurality of energy storage elements illustrated or described may include portions of larger energy storage elements such as five battery modules housed within one battery pack. For example, and without limitation, first energy storage element 304 may include more than one battery modules housed within one battery pack, a second energy storage element may include a single battery module housed within the same battery pack, and a third energy storage element may include an entire battery pack. One of ordinary skill in the art will appreciate the vast arrangements of energy storage elements and the respective capacities thereof.

With continued reference to FIG. 3B, exemplary embodiment of system 300 may include a bus element 308. Bus element 308 may be consistent with any bus element as described in this disclosure. Bus element 308 may be any manner of conductive material configured to convey electrical energy in any form as described in this disclosure between components. For example, and without limitation, bus element 308 may include any number of components electrically connected thereto, including circuit elements, energy storage elements, propulsors, flight control components, one or more computing devices, sensors, or combination thereof, among others. Bus element 308 may include a plurality of wires or conductive strips, bars, structures, or a combination thereof. Bus element 308 may be configured to convey electrical energy configured to power one or more other components electrically connected thereto and/or be configured to convey electrical energy configured to transmit signals between one or more components.

With continued reference to FIG. 3B, exemplary embodiment of system 300 may include a cross tie element 312. Cross tie element 312 may be consistent with any cross tie element as described in this disclosure. Cross tie element 312 may include any electrical switches, relays, components, or combinations thereof. Cross tie element 312 may be electrically connected to bus element 308 and through said bus element 308 may be electrically and communicatively connected to any one or more components as described in this disclosure, namely any of the plurality of energy storage elements such as first energy storage element 304. Cross tie element 312 may be configured to receive one or more electrical signals configured to open or close cross tie element 312. Cross tie element 312, through said opening and closing may electrically disconnect or connect, respectively, first energy storage element from second energy storage element or plurality of energy storage elements as described in this disclosure.

With continued reference to FIG. 3B, exemplary embodiment of system 300 may include a propulsor 316. Propulsor 316 may be electrically and communicatively connected to any of the plurality of other components as described in this disclosure through bus element 308. Propulsor 316 may be one of a plurality of propulsors as described in this disclosure. For example, and without limitation, propulsor 316 may include an electric motor, an actuator consistent with any actuator as described in this disclosure, one or more computing devices, or any other propulsor configured to manipulate a fluid medium.

With continued reference to FIG. 3B, exemplary embodiment of system 300 may include a fuse 320. Fuse 320 may be consistent with any fuse as described in this disclosure. In general, and for the purposes of this disclosure, a fuse is an electrical safety device that operate to provide overcurrent protection of an electrical circuit. As a sacrificial device, its essential component may be metal wire or strip that melts when too much current flows through it, thereby interrupting energy flow. Fuse 320 may include a thermal fuse, mechanical fuse, blade fuse, expulsion fuse, spark gap surge arrestor, varistor, or a combination thereof. Fuse 320 may be implemented in any number of arrangements and at any point or points within exemplary embodiment of system 300. Fuse 320 may be included between plurality of energy storage elements, propulsors, cross tie elements, or any other component electrically connected to bus element 308. Fuse 320 may be implemented between any other electrical components connected anywhere or in any system comprised by the herein disclosed embodiments.

Referring now to FIG. 3C, exemplary embodiments of graphs representing power capability vs. depth of charge is presented. There are two distinct graphical representations of the values discussed herein. Referring specifically to graph 324, the y-axis is Power Capability measured in Watts (W) and the x-axis is Depth of Discharge. Graph 324 represents two energy storage elements as represented by the two curves in the field of the graph. One of ordinary skill in the art would appreciate that the two curves represent two energy storage elements discharge uniformly. For the purposes of this disclosure, “uniform discharge” is the flow of energy out of an energy storage element at the same rate measured in one or more electrical parameters such as current or voltage, among others. The vertical line represents a certain depth of discharge and the intersection with the curves shows the relative power capability of the two energy storage elements. It may be readily seen from graph 324 that the power capability of the two energy storage elements may not be equal at the same depth of discharge. For the purposes of this disclosure, “depth of discharge” is the amount of energy depleted from an energy storage element. For example, a greater depth of discharge leaves less energy remaining in the energy storage element than a lesser depth of discharge. The energy storage element may be consistent with any energy storage element as described in this disclosure.

With continued reference to FIG. 3C, graph 328 is presented representing two curves measuring Power Capability (W) versus Depth of Discharge. As one of ordinary skill in the art would appreciate, the two curves in the field of graph 328 represented biased, or uneven discharge of two energy storage elements. The biased discharge may be biased as a function of modulation of one or more electrical commands as described in this disclosure. When biased discharging is utilized, two different depth of charges of the two energy storage elements renders the same power capability of the two energy storage elements. That is to say that although one energy storage element undergoes a greater depth of discharge, the same power capability may be seen from the two energy storage elements. Biased discharge may be a function of pilot commands, one or more computing devices, elements of data generated by any of the systems and methods as described in this disclosure, machine-learning processes, optimization processes, emergency procedures, a combination thereof, or the like.

Referring now to FIG. 4A, exemplary embodiment of system 400 is represented in schematic form. System 400 may include a first energy storage element 404. First energy storage element 404 may be consistent with any energy storage element as described in this disclosure. For example, and without limitation, first energy storage element 404 may include a plurality of battery packs, battery modules, battery cells, or other types of energy storage elements electrically connected together in series and/or parallel. One of ordinary skill in the art would appreciate that there are five energy storage elements illustrated in FIG. 4A, however, any number of energy storage elements may be included in system and operate according to the herein described methodology. For example, and without limitation, first energy storage element 404 and any of the plurality of energy storage elements illustrated or described may include portions of larger energy storage elements such as five battery modules housed within one battery pack. For example, and without limitation, first energy storage element 404 may include more than one battery modules housed within one battery pack, a second energy storage element may include a single battery module housed within the same battery pack, and a third energy storage element may include an entire battery pack. One of ordinary skill in the art will appreciate the vast arrangements of energy storage elements and the respective capacities thereof.

With continued reference to FIG. 4A, exemplary embodiment of system 400 may include a bus element 408. Bus element 408 may be consistent with any bus element as described in this disclosure. Bus element 408 may be any manner of conductive material configured to convey electrical energy in any form as described in this disclosure between components. For example, and without limitation, bus element 408 may include any number of components electrically connected thereto, including circuit elements, energy storage elements, propulsors, flight control components, one or more computing devices, sensors, or combination thereof, among others. Bus element 308 may include a plurality of wires or conductive strips, bars, structures, or a combination thereof. Bus element 308 may be configured to convey electrical energy configured to power one or more other components electrically connected thereto and/or be configured to convey electrical energy configured to transmit signals between one or more components.

With continued reference to FIG. 4A, exemplary embodiment of system may 400 include a cross tie element 412. Cross tie element 412 may be consistent with any cross tie element as described in this disclosure. Cross tie element 412 may include any electrical switches, relays, components, or combinations thereof. Cross tie element 412 may be electrically connected to bus element 408 and through said bus element 408 may be electrically and communicatively connected to any one or more components as described in this disclosure, namely any of the plurality of energy storage elements such as first energy storage element 404. Cross tie element 412 may be configured to receive one or more electrical signals configured to open or close cross tie element 412. Cross tie element 412, through said opening and closing may electrically disconnect or connect, respectively, first energy storage element from second energy storage element or plurality of energy storage elements as described in this disclosure.

With continued reference to FIG. 4A, exemplary embodiment of system 400 may include a propulsor 416. Propulsor 416 may be electrically and communicatively connected to any of the plurality of other components as described in this disclosure through bus element 408. Propulsor 416 may be one of a plurality of propulsors as described in this disclosure. For example, and without limitation, propulsor 316 may include an electric motor, an actuator consistent with any actuator as described in this disclosure, one or more computing devices, or any other propulsor configured to manipulate a fluid medium.

With continued reference to FIG. 4A, exemplary embodiment of system 400 may include a fuse 420. Fuse 420 may be consistent with any fuse as described in this disclosure. In general, and for the purposes of this disclosure, a fuse is an electrical safety device that operate to provide overcurrent protection of an electrical circuit. As a sacrificial device, its essential component may be metal wire or strip that melts when too much current flows through it, thereby interrupting energy flow. Fuse 420 may include a thermal fuse, mechanical fuse, blade fuse, expulsion fuse, spark gap surge arrestor, varistor, or a combination thereof. Fuse 420 may be implemented in any number of arrangements and at any point or points within exemplary embodiment of system 400. Fuse 420 may be included between plurality of energy storage elements, propulsors, cross tie elements, or any other component electrically connected to bus element 408. Fuse 420 may be implemented between any other electrical components connected anywhere or in any system comprised by the herein disclosed embodiments.

Referring now to FIG. 4B, graph 424 is presented representing Mission Power Demand on the y-axis and Time into Mission on the x-axis. There are three curves shown in the field of graph 424. The closed cross tie curve 428 represents the power demanded by the plurality of propulsors from the plurality of energy storage elements during various phases of flight (e.g. the mission) including take-off, climb, cruise, descent, and landing. One of ordinary skill in the art would appreciate that graph 424 represents conventional take-off and landing electric vehicles, such as the aircraft described herein below in one of its dual modes. First open cross tie curve 432 and second open cross tie curve 436 represent the power demanded by the plurality of propulsors from a first and second portion of energy storage elements, respectively, over various phases of flight (e.g. the mission). First open cross tie curve 432 demands less power in all phases of flight than closed cross tie curve 428. One of ordinary skill in the art would appreciate that modulating the command for discharge of the first and second energy storage elements (as shown by the repeating pattern in the “cruise” section of graph 424 consistent with the description herein produces a varying and opposite power demand in first open cross tie curve 432 and second open cross tie curve 436. In other words, modulating the demand for power of a first energy storage element produces an opposite demand in a second energy storage element.

With continued reference to FIG. 4B, graph 424 may include a power demand for each propulsor of the plurality of propulsors as described in this disclosure. a power demand of each propulsor of a plurality of propulsors may be calculated for at least a future phase of flight. Power demand may be calculated using one or more of various factors, including without limitation manufacture supplied data for propulsor, engine and/or motor. In an embodiment, factors used to calculate the power demand calculation may use weight and/or payload of aircraft in addition to manufacturing data. Power demand, as a non-limiting example, may be a function of such elements as a required speed of the propulsor for any phase of flight, weight or payload, altitude, temperature, weather, environmental conditions, and/or size, type and or shape of a propeller blade, rotor blade, and/or other propulsor blade. Power demand may alternatively or additionally, without limitation, be a function of a type, size and age of one or more motors driving or incorporated in plurality of propulsors. As a non-limiting example, power demand may be calculated for a portion of the flight and/or the entire phase of a flight, flight plan, or mission. As another example and without limitation, power demand of at least a propulsor of a plurality of propulsors, at a point of time or for the remaining time of the particular phase of flight may be calculated. As another example and without limitation, power demand may be calculated for each individual propulsor during a phase of flight or for the entire flight plan. As another example and without limitation, power demand may be calculated for the plurality of propulsors and divided by the number of propulsors for a phase of flight of the entire flight plan. As another example and without limitation, power demand for an individual propulsor or a plurality of propulsors may be done at any part of the flight or flight plan and may be done multiple times during flight or the mission.

Referring now to FIG. 5 , an exemplary embodiment of battery module 500 is illustrated. In embodiments, each circle illustrated represents a battery cell's circular cross-section. A battery cell, which will be adequately described below may take a plurality of forms, but for the purposes of these illustrations and disclosure, will be represented by a cylinder, with circles in representing the cross section of one cell each. With this orientation, a cylindrical battery cell has a long axis not visible in illustration. Battery cells are disposed in a staggered arrangement, with one battery unit including two columns of staggered cells. Each battery unit includes at least the cell retainer including a sheet of material with holes in a staggered pattern corresponding to the staggered orientation of cells. Cell retainer may be the component which fixes the battery cells in their orientation amongst the entirety of the battery module. Cell retainer also includes two columns of staggered holes corresponding to the battery cells. Cell guide may be disposed between each set of two columns of the battery cells underneath the cell retainer. Battery module can include a protective wrapping which weaves in between the two columns of the battery cells contained in a battery unit.

With continued reference to FIG. 5 , battery module 500 may include a sense board, a side panel, an end cap, electrical bus, and openings are presented. A sense board may include at least a portion of a circuit board that includes one or more sensors configured to measure the temperature of the battery cells disposed within battery module 500. In embodiments, sensor board may include one or more openings disposed in rows and column on a surface of sense board. In embodiments, each hole may correspond to the battery cells disposed within, encapsulated, at least in part, by battery units. For example, the location of each hole may correspond to the location of each battery cell disposed within battery module 500.

Referring still to FIG. 5 , according to embodiment, battery module 500 can include one or more side panels. A side panel can include a protective layer of material configured to create a barrier between internal components of battery module 500 and other aircraft components or environment. A side panel may include opposite and opposing faces that form a side of and encapsulate at least a portion of battery module 500. A side panel may include metallic materials like aluminum, aluminum alloys, steel alloys, copper, tin, titanium, another undisclosed material, or a combination thereof. A side panel may not preclude use of nonmetallic materials alone or in combination with metallic components permanently or temporarily coupled together. Nonmetallic materials that may be used alone or in combination in the construction of a side panel may include high density polyethylene (HDPE), polypropylene, polycarbonate, acrylonitrile butadiene styrene, polyethylene, nylon, polystyrene, polyether ether ketone, to name a few. A side panel may be manufactured by a number of processes alone or in combination, including but limited to, machining, milling, forging, casting, 3D printing (or other additive manufacturing methods), turning, or injection molding, to name a few. One of ordinary skill in the art would appreciate that a side panel may be manufactured in pieces and assembled together by screws, nails, rivets, dowels, pins, epoxy, glue, welding, crimping, or another undisclosed method alone or in combination. A side panel may be coupled to sense board, the back plate, and/or an end cap through standard hardware like a bolt and nut mechanism, for example.

With continued reference to FIG. 5 , battery module 500 may also include one or more end caps. An end cap may include a nonconductive component configured to align the back plate, sense board, and internal battery components of battery module 500 and hold their position. An end cap may form and end of and encapsulate a portion of a first end of battery module 500 and a second opposite and opposing end cap may form a second end and encapsulate a portion of a second end of battery module 500. An end cap may include a snap attachment mechanism further including a protruding boss which can configured to be captured, at least in part by a receptable of a corresponding size, by a receptacle disposed in or on the back plate. An end cap may employ a similar or same method for coupling itself to sense board, which may include a similar or the same receptacle. One or ordinary skill in the art would appreciate that the embodiments of a quick attach/detach mechanism end cap may be only an example and any number of mechanisms and methods may be used for this purpose. It should also be noted that other mechanical connecting mechanisms may be used that are not necessarily designed for quick removal. Said mechanical connecting may include, as a non-limiting example, rigid coupling (e.g. beam coupling), bellows coupling, bushed pin coupling, constant velocity, split-muff coupling, diaphragm coupling, disc coupling, donut coupling, elastic coupling, flexible coupling, fluid coupling, gear coupling, grid coupling, hirth joints, hydrodynamic coupling, jaw coupling, magnetic coupling, Oldham coupling, sleeve coupling, tapered shaft lock, twin spring coupling, rag joint coupling, universal joints, or any combination thereof. An end cap may include a nonconductive component manufactured from or by a process that renders it incapable or unsuitable for conveying electrical through, on, or over it. Nonconductive materials an end cap may include may be paper, Teflon, glass, rubber, fiberglass, porcelain, ceramic, quartz, various plastics like HDPE, ABS, among others alone or in combination.

Still referring to FIG. 5 , an end cap may include an electrical bus. An electrical bus, for the purposes of this disclosure and in electrical parlance is any common connection to which any number of loads, which may be connected in parallel, and share a relatively similar voltage may be electrically coupled. Electrical bus may refer to power busses, audio busses, video busses, computing address busses, and/or data busses. Electrical bus may be responsible for conveying electrical energy stored in battery module 500 to at least a portion of an eVTOL aircraft. The same or a distinct electrical bus may additionally or alternatively responsible for conveying electrical signals generated by any number of components within battery module 500 to any destination on or offboard an eVTOL aircraft. An end cap may include wiring or conductive surfaces only in portions required to electrically couple electrical bus to electrical power or necessary circuits to convey that power or signals to their destinations.

Still referring to FIG. 5 , and in embodiments, a battery module with multiple battery units is illustrated, according to embodiments. Battery module 500 may include a battery cell, the cell retainer, a cell guide, a protective wrapping, a back plate, an end cap, and a side panel. Battery module 500 may include a plurality of the battery cells. In embodiments, the battery cells may be disposed and/or arranged within a respective battery unit in groupings of any number of columns and rows. For example, in the illustrative embodiment of FIG. 5 , the battery cells are arranged in each respective battery unit with 18 cells in two columns. It should be noted that although the illustration may be interpreted as containing rows and columns, that the groupings of the battery cells in a battery unit, that the rows are only present as a consequence of the repetitive nature of the pattern of staggered the battery cells and battery cell holes in the cell retainer being aligned in a series. While in the illustrative embodiment of FIG. 5 the battery cells are arranged 18 to a battery unit with a plurality of battery units including battery module 500, one of skill in the art will understand that the battery cells may be arranged in any number to a row and in any number of columns and further, any number of battery units may be present in battery module 500. According to embodiments, the battery cells within a first column may be disposed and/or arranged such that they are staggered relative to the battery cells within a second column. In this way, any two adjacent rows of the battery cells may not be laterally adjacent but instead may be respectively offset a predetermined distance. In embodiments, any two adjacent rows of the battery cells may be offset by a distance equal to a radius of a battery cell. This arrangement of the battery cells is only a non-limiting example and in no way preclude other arrangement of the battery cells.

Battery module 500 may also include a protective wrapping woven between the plurality of the battery cells. Protective wrapping may provide fire protection, thermal containment, and thermal runaway during a battery cell malfunction or within normal operating limits of one or more the battery cells and/or potentially, battery module 500 as a whole. Battery module 500 may also include a backplate. A backplate may be configured to provide structure and encapsulate at least a portion of the battery cells, the cell retainers, the cell guides, and protective wraps. End cap may be configured to encapsulate at least a portion of the battery cells, the cell retainers, the cell guides, and battery units, as will be discussed further below, end cap may include a protruding boss that clicks into receivers in both ends of the back plate, as well as a similar boss on a second end that clicks into sense board. Side panel may provide another structural element with two opposite and opposing faces and further configured to encapsulate at least a portion of the battery cells, the cell retainers, the cell guides, and battery units.

In embodiments, battery module 500 can include one or more the battery cells. In another embodiment, battery module 500 includes a plurality of individual the battery cells. Battery cells may each include a cell configured to include an electrochemical reaction that produces electrical energy sufficient to power at least a portion of an eVTOL aircraft. Battery cell may include electrochemical cells, galvanic cells, electrolytic cells, fuel cells, flow cells, voltaic cells, or any combination thereof—to name a few. In embodiments, the battery cells may be electrically connected in series, in parallel, or a combination of series and parallel. Series connection, as used herein, includes wiring a first terminal of a first cell to a second terminal of a second cell and further configured to include a single conductive path for electricity to flow while maintaining the same current (measured in Amperes) through any component in the circuit. Battery cells may use the term ‘wired’, but one of ordinary skill in the art would appreciate that this term is synonymous with ‘electrically connected’, and that there are many ways to couple electrical elements like the battery cells together. As an example, the battery cells can be coupled via prefabricated terminals of a first gender that mate with a second terminal with a second gender. Parallel connection, as used herein, includes wiring a first and second terminal of a first battery cell to a first and second terminal of a second battery cell and further configured to include more than one conductive path for electricity to flow while maintaining the same voltage (measured in Volts) across any component in the circuit. Battery cells may be wired in a series-parallel circuit which combines characteristics of the constituent circuit types to this combination circuit. Battery cells may be electrically connected in any arrangement which may confer onto the system the electrical advantages associated with that arrangement such as high-voltage applications, high-current applications, or the like. As used herein, an electrochemical cell may be a device capable of generating electrical energy from chemical reactions or using electrical energy to cause chemical reactions. Further, voltaic or galvanic cells are electrochemical cells that generate electric current from chemical reactions, while electrolytic cells generate chemical reactions via electrolysis. As used herein, the term ‘battery’ may be used as a collection of cells connected in series or parallel to each other. Cell retainer may employ a staggered arrangement to allow more cells to be disposed closer together than in square columns and rows like in a grid pattern. The staggered arrangement may also be configured to allow better thermodynamic dissipation, the methods of which may be further disclosed hereinbelow. Cell retainer may include staggered openings that align with the battery cells and further configured to hold the battery cells in fixed positions. Cell retainer may include an injection molded component. Injection molded component may include a component manufactured by injecting a liquid into a mold and letting it solidify, taking the shape of the mold in its hardened form. Cell retainer may include liquid crystal polymer, polypropylene, polycarbonate, acrylonitrile butadiene styrene, polyethylene, nylon, polystyrene, polyether ether ketone, to name a few. Cell retainer may include a second the cell retainer fixed to the second end of the battery cells and configured to hold the battery cells in place from both ends. Second cell retainer may include similar or the exact same characteristics and functions of first the cell retainer. Battery module 500 may also include the cell guide. In embodiments, cell guide can be configured to distribute heat that may be generated by the battery cells. According to embodiments, battery module 500 may also include the back plate. Back plate may be configured to provide a base structure for battery module 500 and may encapsulate at least a portion thereof. Backplate can have any shape and includes opposite, opposing sides with a thickness between them. In embodiments, the back plate may include an effectively flat, rectangular prism shaped sheet. For example, the back plate can include one side of a larger rectangular prism which characterizes the shape of battery module 500 as a whole. Back plate also includes openings correlating to each battery cell of the plurality of the battery cells. Back plate may include a lamination of multiple layers. The layers that are laminated together may include FR-4, a glass-reinforced epoxy laminate material, and a thermal barrier of a similar or exact same type as disclosed hereinabove. Back plate may be configured to provide structural support and containment of at least a portion of battery module 500 as well as provide fire and thermal protection. According to embodiments, battery module 500 may also include an end cap configured to encapsulate at least a portion of battery module 500. End cap may provide structural support for battery module 500 and hold the back plate in a fixed relative position compared to the overall battery module 500. End cap may include a protruding boss on a first end that mates up with and snaps into a receiving feature on a first end of the back plate. End cap may include a second protruding boss on a second end that mates up with and snaps into a receiving feature on the sense board. Battery module 500 may also include at least a side panel that may encapsulate two sides of battery module 500. Any side panel may include opposite and opposing faces including a metal or composite material. Side panel(s) may provide structural support for battery module 500 and provide a barrier to separate battery module 500 from exterior components within aircraft or environment.

With continued reference to FIG. 5 , any of the disclosed systems, namely battery module 500 or one or more battery packs may incorporate provisions to dissipate heat energy present due to electrical resistance in integral circuit. Battery module 500 includes one or more battery modules wired in series and/or parallel. The presence of a voltage difference and associated amperage inevitably will increase heat energy present in and around battery module 500 as a whole. The presence of heat energy in a power system is potentially dangerous by introducing energy possibly sufficient to damage mechanical, electrical, and/or other systems present in at least a portion of exemplary aircraft 700. Battery module 500 may include mechanical design elements, one of ordinary skill in the art, may thermodynamically dissipate heat energy away from battery module 500. The mechanical design may include, but is not limited to, slots, fins, heat sinks, perforations, a combination thereof, or another undisclosed element.

With continued reference to FIG. 5 , heat dissipation may include material selection beneficial to move heat energy in a suitable manner for operation of battery module 500. Certain materials with specific atomic structures and therefore specific elemental or alloyed properties and characteristics may be selected in construction of battery module 500 to transfer heat energy out of a vulnerable location or selected to withstand certain levels of heat energy output that may potentially damage an otherwise unprotected component. One of ordinary skill in the art, after reading the entirety of this disclosure would understand that material selection may include titanium, steel alloys, nickel, copper, nickel-copper alloys such as Monel, tantalum and tantalum alloys, tungsten and tungsten alloys such as Inconel, a combination thereof, or another undisclosed material or combination thereof.

With continued reference to FIG. 5 , heat dissipation may include a combination of mechanical design and material selection. The responsibility of heat dissipation may fall upon the material selection and design as disclosed above in regard to any component disclosed in this paper. Battery module 500 may include similar or identical features and materials ascribed to battery module 500 in order to manage the heat energy produced by these systems and components.

With continued reference to FIG. 5 , according to embodiments, the circuitry battery module 500 may include, as discussed above, may be shielded from electromagnetic interference. The battery pack, battery modules, and/or battery elements and associated circuitry may be shielded by material such as mylar, aluminum, copper a combination thereof, or another suitable material. Battery module 500 and associated circuitry may include one or more of the aforementioned materials in their inherent construction or additionally added after manufacture for the express purpose of shielding a vulnerable component. Battery module 500 and associated circuitry may alternatively or additionally be shielded by location. Electrochemical interference shielding by location includes a design configured to separate a potentially vulnerable component from energy that may compromise the function of said component. The location of vulnerable component may be a physical uninterrupted distance away from an interfering energy source, or location configured to include a shielding element between energy source and target component. The shielding may include an aforementioned material in this section, a mechanical design configured to dissipate the interfering energy, and/or a combination thereof. The shielding including material, location and additional shielding elements may defend a vulnerable component from one or more types of energy at a single time and instance or include separate shielding for individual potentially interfering energies.

With continued reference to FIG. 5 , battery module 500 may be a portion of a battery pack, the battery pack may be a power source configured to store electrical energy in the form of a plurality of battery modules, which themselves are included of a plurality of electrochemical cells. These cells may utilize electrochemical cells, galvanic cells, electrolytic cells, fuel cells, flow cells, and/or voltaic cells. In general, an electrochemical cell is a device capable of generating electrical energy from chemical reactions or using electrical energy to cause chemical reactions, this disclosure will focus on the former. Voltaic or galvanic cells are electrochemical cells that generate electric current from chemical reactions, while electrolytic cells generate chemical reactions via electrolysis. In general, the term ‘battery’ is used as a collection of cells connected in series or parallel to each other. A battery cell may, when used in conjunction with other cells, may be electrically connected in series, in parallel or a combination of series and parallel. Series connection includes wiring a first terminal of a first cell to a second terminal of a second cell and further configured to include a single conductive path for electricity to flow while maintaining the same current (measured in Amperes) through any component in the circuit. A battery cell may use the term ‘wired’, but one of ordinary skill in the art would appreciate that this term is synonymous with ‘electrically connected’, and that there are many ways to couple electrical elements like the battery cells together. An example of a connector that do not include wires may be prefabricated terminals of a first gender that mate with a second terminal with a second gender. Battery cells may be wired in parallel. Parallel connection includes wiring a first and second terminal of a first battery cell to a first and second terminal of a second battery cell and further configured to include more than one conductive path for electricity to flow while maintaining the same voltage (measured in Volts) across any component in the circuit. Battery cells may be wired in a series-parallel circuit which combines characteristics of the constituent circuit types to this combination circuit. Battery cells may be electrically connected in a virtually unlimited arrangement which may confer onto the system the electrical advantages associated with that arrangement such as high-voltage applications, high-current applications, or the like. In an exemplary embodiment, the battery pack include 196 battery cells in series and 18 battery cells in parallel. This is, as someone of ordinary skill in the art would appreciate, is only an example and the battery pack may be configured to have a near limitless arrangement of battery cell configurations.

With continued reference to FIG. 5 , a battery pack may include a plurality of battery modules 500. Battery modules 500 may be wired together in series and in parallel. Battery pack may include center sheet which may include a thin barrier. The barrier may include a fuse connecting battery modules on either side of center sheet. The fuse may be disposed in or on center sheet and configured to connect to an electric circuit including a first battery module and therefore battery unit and cells. In general, and for the purposes of this disclosure, a fuse is an electrical safety device that operate to provide overcurrent protection of an electrical circuit. As a sacrificial device, its essential component may be metal wire or strip that melts when too much current flows through it, thereby interrupting energy flow. Fuse may include a thermal fuse, mechanical fuse, blade fuse, expulsion fuse, spark gap surge arrestor, varistor, or a combination thereof. Battery pack may also include a side wall includes a laminate of a plurality of layers configured to thermally insulate the plurality of battery modules from external components of the battery pack. Side wall layers may include materials which possess characteristics suitable for thermal insulation as described in the entirety of this disclosure like fiberglass, air, iron fibers, polystyrene foam, and thin plastic films, to name a few. Side wall may additionally or alternatively electrically insulate the plurality of battery modules from external components of the battery pack and the layers of which may include polyvinyl chloride (PVC), glass, asbestos, rigid laminate, varnish, resin, paper, Teflon, rubber, and mechanical lamina. Center sheet may be mechanically coupled to side wall in any manner described in the entirety of this disclosure or otherwise undisclosed methods, alone or in combination. Side wall may include a feature for alignment and coupling to center sheet. This feature may include a cutout, slots, holes, bosses, ridges, channels, and/or other undisclosed mechanical features, alone or in combination. Battery pack may also include the end panel including a plurality of electrical connectors and further configured to fix the battery pack in alignment with at least a side wall. End panel may include a plurality of electrical connectors of a first gender configured to electrically and mechanically couple to electrical connectors of a second gender. End panel may be configured to convey electrical energy from the battery cells to at least a portion of an eVTOL aircraft. Electrical energy may be configured to power at least a portion of an eVTOL aircraft or include signals to notify aircraft computers, personnel, users, pilots, and any others of information regarding battery health, emergencies, and/or electrical characteristics. The plurality of electrical connectors may include blind mate connectors, plug and socket connectors, screw terminals, ring and spade connectors, blade connectors, and/or an undisclosed type alone or in combination. The electrical connectors of which the end panel includes may be configured for power and communication purposes. A first end of the end panel may be configured to mechanically couple to a first end of a first side wall by a snap attachment mechanism, similar to end cap and side panel configuration utilized in the battery module. To reiterate, a protrusion disposed in or on the end panel may be captured, at least in part, by a receptacle disposed in or on side wall. A second end of the end panel may be mechanically coupled to a second end of a second side wall in a similar or the same mechanism.

Referring now to FIG. 6 , system 100, processor, or another computing device or model may utilize stored data to generate any datum as described in this disclosure. Stored data may be past status datums, charge datums, health datums, or the like in an embodiment of the present invention. Stored data may be input by a user, pilot, support personnel, or another. Stored data may include algorithms and machine-learning processes that may generate one or more datums associated with the herein disclosed system including charge datums, health datums, and the like. The algorithms and machine-learning processes may be any algorithm or machine-learning processes as described in this disclosure. Training data may be columns, matrices, rows, blocks, spreadsheets, books, or other suitable datastores or structures that contain correlations between past status datums, health datums, or the like to useful life estimates. Training data may be any training data as described below. Training data may be past measurements detected by any sensors described herein or another sensor or suite of sensors in combination. Training data may be detected by onboard or offboard instrumentation designed to detect status datum or environmental conditions as described in this disclosure. Training data may be uploaded, downloaded, and/or retrieved from a server prior to flight. Training data may be generated by a computing device that may simulate input datums suitable for use by the processor, flight controller, controller, or other computing devices in an embodiment of the present invention. Processor, flight controller, controller, and/or another computing device as described in this disclosure may train one or more machine-learning models using the training data as described in this disclosure. Training one or more machine-learning models consistent with the training one or more machine learning modules as described in this disclosure.

With continued reference to FIG. 6 , algorithms and machine-learning processes may include any algorithms or machine-learning processes as described in this disclosure. Training data may be columns, matrices, rows, blocks, spreadsheets, books, or other suitable datastores or structures that contain correlations between torque measurements to obstruction datums. Training data may be any training data as described in this disclosure. Training data may be past measurements detected by any sensors described herein or another sensor or suite of sensors in combination. Training data may be detected by onboard or offboard instrumentation designed to detect environmental conditions and measured state datums as described in this disclosure. Training data may be uploaded, downloaded, and/or retrieved from a server prior to flight. Training data may be generated by a computing device that may simulate predictive datums, performance datums, or the like suitable for use by the processor, flight controller, controller, plant model, in an embodiment of the present invention. Processor, flight controller, controller, and/or another computing device as described in this disclosure may train one or more machine-learning models using the training data as described in this disclosure.

Still referring to FIG. 6 , an exemplary embodiment of a machine-learning module 600 that may perform one or more machine-learning processes as described in this disclosure may be illustrated. Machine-learning module may perform determinations, classification, and/or analysis steps, methods, processes, or the like as described in this disclosure using machine learning processes. A “machine learning process,” as used in this disclosure, may be a process that automatedly uses training data 604 to generate an algorithm that will be performed by a computing device/module to produce outputs 608 given data provided as inputs 612; this may be in contrast to a non-machine learning software program where the commands to be executed are determined in advance by a user and written in a programming language.

Still referring to FIG. 6 , “training data,” as used herein, may be data containing correlations that a machine-learning process may use to model relationships between two or more categories of data elements. For instance, and without limitation, training data 604 may include a plurality of data entries, each entry representing a set of data elements that were recorded, received, and/or generated together; data elements may be correlated by shared existence in a given data entry, by proximity in a given data entry, or the like. Multiple data entries in training data 604 may evince one or more trends in correlations between categories of data elements; for instance, and without limitation, a higher value of a first data element belonging to a first category of data element may tend to correlate to a higher value of a second data element belonging to a second category of data element, indicating a possible proportional or other mathematical relationship linking values belonging to the two categories. Multiple categories of data elements may be related in training data 604 according to various correlations; correlations may indicate causative and/or predictive links between categories of data elements, which may be modeled as relationships such as mathematical relationships by machine-learning processes as described in further detail below. Training data 604 may be formatted and/or organized by categories of data elements, for instance by associating data elements with one or more descriptors corresponding to categories of data elements. As a non-limiting example, training data 604 may include data entered in standardized forms by persons or processes, such that entry of a given data element in a given field in a form may be mapped to one or more descriptors of categories. Elements in training data 604 may be linked to descriptors of categories by tags, tokens, or other data elements; for instance, and without limitation, training data 604 may be provided in fixed-length formats, formats linking positions of data to categories such as comma-separated value (CSV) formats and/or self-describing formats such as extensible markup language (XML), JavaScript Object Notation (JSON), or the like, enabling processes or devices to detect categories of data.

Alternatively, or additionally, and continuing to refer to FIG. 6 , training data 604 may include one or more elements that are not categorized; that may be, training data 604 may not be formatted or contain descriptors for some elements of data. Machine-learning algorithms and/or other processes may sort training data 604 according to one or more categorizations using, for instance, natural language processing algorithms, tokenization, detection of correlated values in raw data and the like; categories may be generated using correlation and/or other processing algorithms. As a non-limiting example, in a corpus of text, phrases making up a number “n” of compound words, such as nouns modified by other nouns, may be identified according to a statistically significant prevalence of n-grams containing such words in a particular order; such an n-gram may be categorized as an element of language such as a “word” to be tracked similarly to single words, generating a new category as a result of statistical analysis. Similarly, in a data entry including some textual data, a person's name may be identified by reference to a list, dictionary, or other compendium of terms, permitting ad-hoc categorization by machine-learning algorithms, and/or automated association of data in the data entry with descriptors or into a given format. The ability to categorize data entries automatedly may enable the same training data 604 to be made applicable for two or more distinct machine-learning algorithms as described in further detail below. Training data 604 used by machine-learning module 600 may correlate any input data as described in this disclosure to any output data as described in this disclosure.

Further referring to FIG. 6 , training data may be filtered, sorted, and/or selected using one or more supervised and/or unsupervised machine-learning processes and/or models as described in further detail below; such models may include without limitation a training data classifier 616. Training data classifier 616 may include a “classifier,” which as used in this disclosure may be a machine-learning model as defined below, such as a mathematical model, neural net, or program generated by a machine learning algorithm known as a “classification algorithm,” as described in further detail below, that sorts inputs into categories or bins of data, outputting the categories or bins of data and/or labels associated therewith. A classifier may be configured to output at least a datum that labels or otherwise identifies a set of data that are clustered together, found to be close under a distance metric as described below, or the like. Machine-learning module 600 may generate a classifier using a classification algorithm, defined as a processes whereby a computing device and/or any module and/or component operating thereon derives a classifier from training data 604. Classification may be performed using, without limitation, linear classifiers such as without limitation logistic regression and/or naive Bayes classifiers, nearest neighbor classifiers such as k-nearest neighbors classifiers, support vector machines, least squares support vector machines, fisher's linear discriminant, quadratic classifiers, decision trees, boosted trees, random forest classifiers, learning vector quantization, and/or neural network-based classifiers. As a non-limiting example, training data classifier 616 may classify elements of training data to classes of deficiencies, wherein a nourishment deficiency may be categorized to a large deficiency, a medium deficiency, and/or a small deficiency.

Still referring to FIG. 6 , machine-learning module 600 may be configured to perform a lazy-learning process 620 and/or protocol, which may alternatively be referred to as a “lazy loading” or “call-when-needed” process and/or protocol, may be a process whereby machine learning may be conducted upon receipt of an input to be converted to an output, by combining the input and training set to derive the algorithm to be used to produce the output on demand. For instance, an initial set of simulations may be performed to cover an initial heuristic and/or “first guess” at an output and/or relationship. As a non-limiting example, an initial heuristic may include a ranking of associations between inputs and elements of training data 604. Heuristic may include selecting some number of highest-ranking associations and/or training data 604 elements. Lazy learning may implement any suitable lazy learning algorithm, including without limitation a K-nearest neighbors algorithm, a lazy naïve Bayes algorithm, or the like; persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various lazy-learning algorithms that may be applied to generate outputs as described in this disclosure, including without limitation lazy learning applications of machine-learning algorithms as described in further detail below.

Alternatively or additionally, and with continued reference to FIG. 6 , machine-learning processes as described in this disclosure may be used to generate machine-learning models 624. A “machine-learning model,” as used in this disclosure, may be a mathematical and/or algorithmic representation of a relationship between inputs and outputs, as generated using any machine-learning process including without limitation any process as described above, and stored in memory; an input is submitted to a machine-learning model 624 once created, which generates an output based on the relationship that was derived. For instance, and without limitation, a linear regression model, generated using a linear regression algorithm, may compute a linear combination of input data using coefficients derived during machine-learning processes to calculate an output datum. As a further non-limiting example, a machine-learning model 624 may be generated by creating an artificial neural network, such as a convolutional neural network including an input layer of nodes, one or more intermediate layers, and an output layer of nodes. Connections between nodes may be created via the process of “training” the network, in which elements from a training data 604 set are applied to the input nodes, a suitable training algorithm (such as Levenberg-Marquardt, conjugate gradient, simulated annealing, or other algorithms) is then used to adjust the connections and weights between nodes in adjacent layers of the neural network to produce the desired values at the output nodes. This process may be sometimes referred to as deep learning.

Still referring to FIG. 6 , machine-learning algorithms may include at least a supervised machine-learning process 628. At least a supervised machine-learning process 628, as defined herein, include algorithms that receive a training set relating a number of inputs to a number of outputs, and seek to find one or more mathematical relations relating inputs to outputs, where each of the one or more mathematical relations may be optimal according to some criterion specified to the algorithm using some scoring function. For instance, a supervised learning algorithm may include status datum as described above as one or more inputs, charge or health datum as an output, and a scoring function representing a desired form of relationship to be detected between inputs and outputs; scoring function may, for instance, seek to maximize the probability that a given input and/or combination of elements inputs may be associated with a given output to minimize the probability that a given input may be not associated with a given output. Scoring function may be expressed as a risk function representing an “expected loss” of an algorithm relating inputs to outputs, where loss is computed as an error function representing a degree to which a prediction generated by the relation may be incorrect when compared to a given input-output pair provided in training data 604. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various possible variations of at least a supervised machine-learning process 628 that may be used to determine relation between inputs and outputs. Supervised machine-learning processes may include classification algorithms as defined above.

Further referring to FIG. 6 , machine learning processes may include at least an unsupervised machine-learning processes 632. An unsupervised machine-learning process, as used herein, is a process that derives inferences in datasets without regard to labels; as a result, an unsupervised machine-learning process may be free to discover any structure, relationship, and/or correlation provided in the data. Unsupervised processes may not require a response variable; unsupervised processes may be used to find interesting patterns and/or inferences between variables, to determine a degree of correlation between two or more variables, or the like.

Still referring to FIG. 6 , machine-learning module 600 may be designed and configured to create a machine-learning model 624 using techniques for development of linear regression models. Linear regression models may include ordinary least squares regression, which aims to minimize the square of the difference between predicted outcomes and actual outcomes according to an appropriate norm for measuring such a difference (e.g. a vector-space distance norm); coefficients of the resulting linear equation may be modified to improve minimization. Linear regression models may include ridge regression methods, where the function to be minimized includes the least-squares function plus term multiplying the square of each coefficient by a scalar amount to penalize large coefficients. Linear regression models may include least absolute shrinkage and selection operator (LASSO) models, in which ridge regression may be combined with multiplying the least-squares term by a factor of 1 divided by double the number of samples. Linear regression models may include a multi-task lasso model wherein the norm applied in the least-squares term of the lasso model may be the Frobenius norm amounting to the square root of the sum of squares of all terms. Linear regression models may include the elastic net model, a multi-task elastic net model, a least angle regression model, a LARS lasso model, an orthogonal matching pursuit model, a Bayesian regression model, a logistic regression model, a stochastic gradient descent model, a perceptron model, a passive aggressive algorithm, a robustness regression model, a Huber regression model, or any other suitable model that may occur to persons skilled in the art upon reviewing the entirety of this disclosure. Linear regression models may be generalized in an embodiment to polynomial regression models, whereby a polynomial equation (e.g. a quadratic, cubic or higher-order equation) providing a best predicted output/actual output fit may be sought; similar methods to those described above may be applied to minimize error functions, as will be apparent to persons skilled in the art upon reviewing the entirety of this disclosure.

Continuing to refer to FIG. 6 , machine-learning algorithms may include, without limitation, linear discriminant analysis. Machine-learning algorithm may include quadratic discriminate analysis. Machine-learning algorithms may include kernel ridge regression. Machine-learning algorithms may include support vector machines, including without limitation support vector classification-based regression processes. Machine-learning algorithms may include stochastic gradient descent algorithms, including classification and regression algorithms based on stochastic gradient descent. Machine-learning algorithms may include nearest neighbors algorithms. Machine-learning algorithms may include Gaussian processes such as Gaussian Process Regression. Machine-learning algorithms may include cross-decomposition algorithms, including partial least squares and/or canonical correlation analysis. Machine-learning algorithms may include naïve Bayes methods. Machine-learning algorithms may include algorithms based on decision trees, such as decision tree classification or regression algorithms. Machine-learning algorithms may include ensemble methods such as bagging meta-estimator, forest of randomized tress, AdaBoost, gradient tree boosting, and/or voting classifier methods. Machine-learning algorithms may include neural net algorithms, including convolutional neural net processes.

With continued reference to FIG. 6 , an “objective function,” as used in this disclosure, is a mathematical function with a solution set including a plurality of data elements to be compared. Mixer may compute a score, metric, ranking, or the like, associated with each performance prognoses and candidate transfer apparatus and select objectives to minimize and/or maximize the score/rank, depending on whether an optimal result may be represented, respectively, by a minimal and/or maximal score; an objective function may be used by mixer to score each possible pairing. At least an optimization problem may be based on one or more objectives, as described below. Mixer may pair a candidate transfer apparatus, with a given combination of performance prognoses, that optimizes the objective function. In various embodiments solving at least an optimization problem may be based on a combination of one or more factors. Each factor may be assigned a score based on predetermined variables. In some embodiments, the assigned scores may be weighted or unweighted. Solving at least an optimization problem may include performing a greedy algorithm process, where optimization may be performed by minimizing and/or maximizing an output of objective function. A “greedy algorithm” is defined as an algorithm that selects locally optimal choices, which may or may not generate a globally optimal solution. For instance, mixer may select objectives so that scores associated therewith are the best score for each goal. For instance, in non-limiting illustrative example, optimization may determine the pitch moment associated with an output of at least a propulsor based on an input.

With continued reference to FIG. 6 , at least an optimization problem may be formulated as a linear objective function, which mixer may optimize using a linear program such as without limitation a mixed-integer program. A “linear program,” as used in this disclosure, is a program that optimizes a linear objective function, given at least a constraint; a linear program maybe referred to without limitation as a “linear optimization” process and/or algorithm. For instance, in non-limiting illustrative examples, a given constraint might be torque limit, and a linear program may use a linear objective function to calculate maximum output based on the limit. In various embodiments, mixer may determine a set of instructions towards achieving a user's goal that maximizes a total score subject to a constraint that there are other competing objectives. A mathematical solver may be implemented to solve for the set of instructions that maximizes scores; mathematical solver may be implemented on mixer and/or another device in flight control system, and/or may be implemented on third-party solver. At least an optimization problem may be formulated as nonlinear least squares optimization process. A “nonlinear least squares optimization process,” for the purposes of this disclosure, is a form of least squares analysis used to fit a set of m observations with a model that is non-linear in n unknown parameters, where m is greater than or equal to n. The basis of the method is to approximate the model by a linear one and to refine the parameters by successive iterations. A nonlinear least squares optimization process may output a fit of signals to at least a propulsor. Solving at least an optimization problem may include minimizing a loss function, where a “loss function” is an expression an output of which a ranking process minimizes to generate an optimal result. As a non-limiting example, mixer may assign variables relating to a set of parameters, which may correspond to score components as described above, calculate an output of mathematical expression using the variables, and select an objective that produces an output having the lowest size, according to a given definition of “size,” of the set of outputs representing each of plurality of candidate ingredient combinations; size may, for instance, included absolute value, numerical size, or the like. Selection of different loss functions may result in identification of different potential pairings as generating minimal outputs.

Referring now to FIG. 7 , an embodiment of an electric aircraft 700 is presented. Still referring to FIG. 7 , electric aircraft 700 may include a vertical takeoff and landing aircraft (eVTOL). As used herein, a vertical take-off and landing (eVTOL) aircraft may be one that can hover, take off, and land vertically. An eVTOL, as used herein, may be an electrically powered aircraft typically using an energy source, of a plurality of energy sources to power the aircraft. In order to optimize the power and energy necessary to propel the aircraft. eVTOL may be capable of rotor-based cruising flight, rotor-based takeoff, rotor-based landing, fixed-wing cruising flight, airplane-style takeoff, airplane-style landing, and/or any combination thereof. Rotor-based flight, as described in this disclosure, may be where the aircraft generated lift and propulsion by way of one or more powered rotors connected with an engine, such as a “quad copter,” multi-rotor helicopter, or other vehicle that maintains its lift primarily using downward thrusting propulsors. Fixed-wing flight, as described in this disclosure, may be where the aircraft may be capable of flight using wings and/or foils that generate life caused by the aircraft's forward airspeed and the shape of the wings and/or foils, such as airplane-style flight. Control forces of the aircraft are achieved by conventional elevators, ailerons and rudders during fixed wing flight. Roll and Pitch control forces on the aircraft are achieved during transition flight by increasing and decreasing torque, and thus thrust on the four lift fans. Increasing torque on both left motors and decreasing torque on both right motors leads to a right roll, for instance. Likewise, increasing the torque on the front motors and decreasing the torque on the rear motors leads to a nose up pitching moment. Clockwise and counterclockwise turning motors torques are increased and decreased to achieve the opposite torque on the overall aircraft about the vertical axis and achieve yaw maneuverability.

With continued reference to FIG. 7 , a number of aerodynamic forces may act upon the electric aircraft 700 during flight. Forces acting on an electric aircraft 700 during flight may include, without limitation, thrust, the forward force produced by the rotating element of the electric aircraft 700 and acts parallel to the longitudinal axis. Another force acting upon electric aircraft 700 may be, without limitation, drag, which may be defined as a rearward retarding force which may be caused by disruption of airflow by any protruding surface of the electric aircraft 700 such as, without limitation, the wing, rotor, and fuselage. Drag may oppose thrust and acts rearward parallel to the relative wind. A further force acting upon electric aircraft 700 may include, without limitation, weight, which may include a combined load of the electric aircraft 700 itself, crew, baggage, and/or fuel. Weight may pull electric aircraft 700 downward due to the force of gravity. An additional force acting on electric aircraft 700 may include, without limitation, lift, which may act to oppose the downward force of weight and may be produced by the dynamic effect of air acting on the airfoil and/or downward thrust from the propulsor of the electric aircraft. Lift generated by the airfoil may depend on speed of airflow, density of air, total area of an airfoil and/or segment thereof, and/or an angle of attack between air and the airfoil. For example, and without limitation, electric aircraft 700 are designed to be as lightweight as possible. Reducing the weight of the aircraft and designing to reduce the number of components may be essential to optimize the weight. To save energy, it may be useful to reduce weight of components of an electric aircraft 700, including without limitation propulsors and/or propulsion assemblies. In an embodiment, the motor may eliminate need for many external structural features that otherwise might be needed to join one component to another component. The motor may also increase energy efficiency by enabling a lower physical propulsor profile, reducing drag and/or wind resistance. This may also increase durability by lessening the extent to which drag and/or wind resistance add to forces acting on electric aircraft 700 and/or propulsors.

Referring still to FIG. 7 , aircraft may include at least a vertical propulsor 704 and at least a forward propulsor 708. A forward propulsor may be a propulsor that propels the aircraft in a forward direction. Forward in this context may be not an indication of the propulsor position on the aircraft; one or more propulsors mounted on the front, on the wings, at the rear, etc. A vertical propulsor may be a propulsor that propels the aircraft in an upward direction; one of more vertical propulsors may be mounted on the front, on the wings, at the rear, and/or any suitable location. A propulsor, as used herein, may be a component or device used to propel a craft by exerting force on a fluid medium, which may include a gaseous medium such as air or a liquid medium such as water. At least a vertical propulsor 704 may be a propulsor that generates a substantially downward thrust, tending to propel an aircraft in a vertical direction providing thrust for maneuvers such as without limitation, vertical take-off, vertical landing, hovering, and/or rotor-based flight such as “quadcopter” or similar styles of flight.

With continued reference to FIG. 7 , at least a forward propulsor 708 as used in this disclosure may be a propulsor positioned for propelling an aircraft in a “forward” direction; at least a forward propulsor may include one or more propulsors mounted on the front, on the wings, at the rear, or a combination of any such positions. At least a forward propulsor may propel an aircraft forward for fixed-wing and/or “airplane”-style flight, takeoff, and/or landing, and/or may propel the aircraft forward or backward on the ground. At least a vertical propulsor 704 and at least a forward propulsor 708 includes a thrust element. At least a thrust element may include any device or component that converts the mechanical energy of a motor, for instance in the form of rotational motion of a shaft, into thrust in a fluid medium. At least a thrust element may include, without limitation, a device using moving or rotating foils, including without limitation one or more rotors, an airscrew or propeller, a set of airscrews or propellers such as contrarotating propellers, a moving or flapping wing, or the like. At least a thrust element may include without limitation a marine propeller or screw, an impeller, a turbine, a pump-jet, a paddle or paddle-based device, or the like. As another non-limiting example, at least a thrust element may include an eight-bladed pusher propeller, such as an eight-bladed propeller mounted behind the engine to ensure the drive shaft may be in compression. Propulsors may include at least a motor mechanically connected to at least a first propulsor as a source of thrust. A motor may include without limitation, any electric motor, where an electric motor may be a device that converts electrical energy into mechanical energy, for instance by causing a shaft to rotate. At least a motor may be driven by direct current (DC) electric power; for instance, at least a first motor may include a brushed DC at least a first motor, or the like. At least a first motor may be driven by electric power having varying or reversing voltage levels, such as alternating current (AC) power as produced by an alternating current generator and/or inverter, or otherwise varying power, such as produced by a switching power source. At least a first motor may include, without limitation, brushless DC electric motors, permanent magnet synchronous at least a first motor, switched reluctance motors, or induction motors. In addition to inverter and/or a switching power source, a circuit driving at least a first motor may include electronic speed controllers or other components for regulating motor speed, rotation direction, and/or dynamic braking. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various devices that may be used as at least a thrust element.

With continued reference to FIG. 7 , during flight, a number of forces may act upon the electric aircraft. Forces acting on an aircraft 700 during flight may include thrust, the forward force produced by the rotating element of the aircraft 700 and acts parallel to the longitudinal axis. Drag may be defined as a rearward retarding force which may be caused by disruption of airflow by any protruding surface of the aircraft 700 such as, without limitation, the wing, rotor, and fuselage. Drag may oppose thrust and acts rearward parallel to the relative wind. Another force acting on aircraft 700 may include weight, which may include a combined load of the aircraft 700 itself, crew, baggage and fuel. Weight may pull aircraft 700 downward due to the force of gravity. An additional force acting on aircraft 700 may include lift, which may act to oppose the downward force of weight and may be produced by the dynamic effect of air acting on the airfoil and/or downward thrust from at least a propulsor. Lift generated by the airfoil may depends on speed of airflow, density of air, total area of an airfoil and/or segment thereof, and/or an angle of attack between air and the airfoil.

With continued reference to FIG. 7 , at least a portion of an electric aircraft may include at least a propulsor. A propulsor, as used herein, may be a component or device used to propel a craft by exerting force on a fluid medium, which may include a gaseous medium such as air or a liquid medium such as water. In an embodiment, when a propulsor twists and pulls air behind it, it will, at the same time, push an aircraft forward with an equal amount of force. The more air pulled behind an aircraft, the greater the force with which the aircraft may be pushed forward. Propulsor may include any device or component that consumes electrical power on demand to propel an electric aircraft in a direction or other vehicle while on ground or in-flight.

With continued reference to FIG. 7 , in an embodiment, at least a portion of the aircraft may include a propulsor, the propulsor may include a propeller, a blade, or any combination of the two. The function of a propeller may be to convert rotary motion from an engine or other power source into a swirling slipstream which pushes the propeller forwards or backwards. Propulsor may include a rotating power-driven hub, to which are attached several radial airfoil-section blades such that the whole assembly rotates about a longitudinal axis. The blade pitch of the propellers may, for example, be fixed, manually variable to a few set positions, automatically variable (e.g. a “constant-speed” type), or any combination thereof. In an embodiment, propellers for an aircraft are designed to be fixed to their hub at an angle similar to the thread on a screw makes an angle to the shaft; this angle may be referred to as a pitch or pitch angle which will determine the speed of the forward movement as the blade rotates.

With continued reference to FIG. 7 , in an embodiment, a propulsor can include a thrust element which may be integrated into the propulsor. Thrust element may include, without limitation, a device using moving or rotating foils, such as one or more rotors, an airscrew or propeller, a set of airscrews or propellers such as contra-rotating propellers, a moving or flapping wing, or the like. Further, a thrust element, for example, can include without limitation a marine propeller or screw, an impeller, a turbine, a pump-jet, a paddle or paddle-based device, or the like.

With continued reference to FIG. 7 , control surfaces may each include any portion of an aircraft that can be moved or adjusted to affect altitude, airspeed velocity, groundspeed velocity or direction during flight. For example, control surfaces may include a component used to affect the aircrafts' roll and pitch which may include one or more ailerons, defined herein as hinged surfaces which form part of the trailing edge of each wing in a fixed wing aircraft, and which may be moved via mechanical means such as without limitation servomotors, mechanical linkages, or the like, to name a few. As a further example, control surfaces may include a rudder, which may include, without limitation, a segmented rudder. Rudder may function, without limitation, to control yaw of an aircraft. Also, control surfaces may include other flight control surfaces such as propulsors, rotating flight controls, or any other structural features which can adjust the movement of the aircraft. A “control surface” as described in this disclosure, is any form of a mechanical linkage with a surface area that interacts with forces to move an aircraft. A control surface may include, as a non-limiting example, ailerons, flaps, leading edge flaps, rudders, elevators, spoilers, slats, blades, stabilizers, stabilators, airfoils, a combination thereof, or any other mechanical surface are used to control an aircraft in a fluid medium. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various mechanical linkages that may be used as a control surface, as used and described in this disclosure.

With continued reference to FIG. 7 , aircraft 700 trajectory is manipulated by one or more control surfaces and propulsors working alone or in tandem consistent with the entirety of this disclosure, hereinbelow. Pitch, roll, and yaw may be used to describe an aircraft's attitude and/or heading, as they correspond to three separate and distinct axes about which the aircraft may rotate with an applied moment, torque, and/or other force applied to at least a portion of an aircraft. “Pitch”, for the purposes of this disclosure refers to an aircraft's angle of attack, that is the difference between the aircraft's nose and the horizontal flight trajectory. For example, an aircraft pitches “up” when its nose is angled upward compared to horizontal flight, like in a climb maneuver. In another example, the aircraft pitches “down”, when its nose is angled downward compared to horizontal flight, like in a dive maneuver. When angle of attack is not an acceptable input to any system disclosed herein, proxies may be used such as pilot controls, remote controls, or sensor levels, such as true airspeed sensors, pitot tubes, pneumatic/hydraulic sensors, and the like. “Roll” for the purposes of this disclosure, refers to an aircraft's position about its longitudinal axis, that is to say that when an aircraft rotates about its axis from its tail to its nose, and one side rolls upward, like in a banking maneuver. “Yaw”, for the purposes of this disclosure, refers to an aircraft's turn angle, when an aircraft rotates about an imaginary vertical axis intersecting the center of the earth and the fuselage of the aircraft. “Throttle”, for the purposes of this disclosure, refers to an aircraft outputting an amount of thrust from a propulsor. Pilot input, when referring to throttle, may refer to a pilot's desire to increase or decrease thrust produced by at least a propulsor. More than one propulsor may be required to adjust torques to accomplish the command to change pitch and yaw, mixer would take in the command and allocate those torques to the appropriate propulsors consistent with the entirety of this disclosure. One of ordinary skill in the art, after reading the entirety of this disclosure, will appreciate the limitless combination of propulsors, flight components, control surfaces, or combinations thereof that could be used in tandem to generate some amount of authority in pitch, roll, yaw, and lift of an electric aircraft consistent with this disclosure.

With continued reference to FIG. 7 , “flight components”, for the purposes of this disclosure, includes components related to, and mechanically connected to an aircraft that manipulates a fluid medium in order to propel and maneuver the aircraft through the fluid medium. The operation of the aircraft through the fluid medium will be discussed at greater length hereinbelow. At least an input datum may include information gathered by one or more sensors. In non-limiting embodiments, flight components may include propulsors, wings, rotors, propellers, pusher propellers, ailerons, elevators, stabilizers, stabilators, and the like, among others.

It is to be noted that any one or more of the aspects and embodiments described herein may be conveniently implemented using one or more machines (e.g., one or more computing devices that are utilized as a user computing device for an electronic document, one or more server devices, such as a document server, etc.) programmed according to the teachings of the present specification, as will be apparent to those of ordinary skill in the computer art. Appropriate software coding can readily be prepared by skilled programmers based on the teachings of the present disclosure, as will be apparent to those of ordinary skill in the software art. Aspects and implementations discussed above employing software and/or software modules may also include appropriate hardware for assisting in the implementation of the machine executable instructions of the software and/or software module.

Such software may be a computer program product that employs a machine-readable storage medium. A machine-readable storage medium may be any medium that is capable of storing and/or encoding a sequence of instructions for execution by a machine (e.g., a computing device) and that causes the machine to perform any one of the methodologies and/or embodiments described herein. Examples of a machine-readable storage medium include, but are not limited to, a magnetic disk, an optical disc (e.g., CD, CD-R, DVD, DVD-R, etc.), a magneto-optical disk, a read-only memory “ROM” device, a random access memory “RAM” device, a magnetic card, an optical card, a solid-state memory device, an EPROM, an EEPROM, and any combinations thereof. A machine-readable medium, as used herein, is intended to include a single medium as well as a collection of physically separate media, such as, for example, a collection of compact discs or one or more hard disk drives in combination with a computer memory. As used herein, a machine-readable storage medium does not include transitory forms of signal transmission.

Such software may also include information (e.g., data) carried as a data signal on a data carrier, such as a carrier wave. For example, machine-executable information may be included as a data-carrying signal embodied in a data carrier in which the signal encodes a sequence of instruction, or portion thereof, for execution by a machine (e.g., a computing device) and any related information (e.g., data structures and data) that causes the machine to perform any one of the methodologies and/or embodiments described herein.

Examples of a computing device include, but are not limited to, an electronic book reading device, a computer workstation, a terminal computer, a server computer, a handheld device (e.g., a tablet computer, a smartphone, etc.), a web appliance, a network router, a network switch, a network bridge, any machine capable of executing a sequence of instructions that specify an action to be taken by that machine, and any combinations thereof. In one example, a computing device may include and/or be included in a kiosk.

FIG. 8 shows a diagrammatic representation of one embodiment of a computing device in the exemplary form of a computer system 800 within which a set of instructions for causing a control system to perform any one or more of the aspects and/or methodologies of the present disclosure may be executed. It is also contemplated that multiple computing devices may be utilized to implement a specially configured set of instructions for causing one or more of the devices to perform any one or more of the aspects and/or methodologies of the present disclosure. Computer system 800 includes a processor 804 and a memory 808 that communicate with each other, and with other components, via a bus 812. Bus 812 may include any of several types of bus structures including, but not limited to, a memory bus, a memory controller, a peripheral bus, a local bus, and any combinations thereof, using any of a variety of bus architectures.

Processor 804 may include any suitable processor, such as without limitation a processor incorporating logical circuitry for performing arithmetic and logical operations, such as an arithmetic and logic unit (ALU), which may be regulated with a state machine and directed by operational inputs from memory and/or sensors; processor 804 may be organized according to Von Neumann and/or Harvard architecture as a non-limiting example. Processor 804 may include, incorporate, and/or be incorporated in, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), Field Programmable Gate Array (FPGA), Complex Programmable Logic Device (CPLD), Graphical Processing Unit (GPU), general purpose GPU, Tensor Processing Unit (TPU), analog or mixed signal processor, Trusted Platform Module (TPM), a floating point unit (FPU), and/or system on a chip (SoC).

Memory 808 may include various components (e.g., machine-readable media) including, but not limited to, a random-access memory component, a read only component, and any combinations thereof. In one example, a basic input/output system 816 (BIOS), including basic routines that help to transfer information between elements within computer system 800, such as during start-up, may be stored in memory 808. Memory 808 may also include (e.g., stored on one or more machine-readable media) instructions (e.g., software) 820 embodying any one or more of the aspects and/or methodologies of the present disclosure. In another example, memory 808 may further include any number of program modules including, but not limited to, an operating system, one or more application programs, other program modules, program data, and any combinations thereof.

Computer system 800 may also include a storage device 824. Examples of a storage device (e.g., storage device 824) include, but are not limited to, a hard disk drive, a magnetic disk drive, an optical disc drive in combination with an optical medium, a solid-state memory device, and any combinations thereof. Storage device 824 may be connected to bus 812 by an appropriate interface (not shown). Example interfaces include, but are not limited to, SCSI, advanced technology attachment (ATA), serial ATA, universal serial bus (USB), IEEE 1394 (FIREWIRE), and any combinations thereof. In one example, storage device 824 (or one or more components thereof) may be removably interfaced with computer system 800 (e.g., via an external port connector (not shown)). Particularly, storage device 824 and an associated machine-readable medium 828 may provide nonvolatile and/or volatile storage of machine-readable instructions, data structures, program modules, and/or other data for computer system 800. In one example, software 820 may reside, completely or partially, within machine-readable medium 828. In another example, software 820 may reside, completely or partially, within processor 804.

Computer system 800 may also include an input device 832. In one example, a user of computer system 800 may enter commands and/or other information into computer system 800 via input device 832. Examples of an input device 832 include, but are not limited to, an alpha-numeric input device (e.g., a keyboard), a pointing device, a joystick, a gamepad, an audio input device (e.g., a microphone, a voice response system, etc.), a cursor control device (e.g., a mouse), a touchpad, an optical scanner, a video capture device (e.g., a still camera, a video camera), a touchscreen, and any combinations thereof. Input device 832 may be interfaced to bus 812 via any of a variety of interfaces (not shown) including, but not limited to, a serial interface, a parallel interface, a game port, a USB interface, a FIREWIRE interface, a direct interface to bus 812, and any combinations thereof. Input device 832 may include a touch screen interface that may be a part of or separate from display 836, discussed further below. Input device 832 may be utilized as a user selection device for selecting one or more graphical representations in a graphical interface as described above.

A user may also input commands and/or other information to computer system 800 via storage device 824 (e.g., a removable disk drive, a flash drive, etc.) and/or network interface device 840. A network interface device, such as network interface device 840, may be utilized for connecting computer system 800 to one or more of a variety of networks, such as network 844, and one or more remote devices 848 connected thereto. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. A network, such as network 844, may employ a wired and/or a wireless mode of communication. In general, any network topology may be used. Information (e.g., data, software 820, etc.) may be communicated to and/or from computer system 800 via network interface device 840.

Computer system 800 may further include a video display adapter 852 for communicating a displayable image to a display device, such as display device 836. Examples of a display device include, but are not limited to, a liquid crystal display (LCD), a cathode ray tube (CRT), a plasma display, a light emitting diode (LED) display, and any combinations thereof. Display adapter 852 and display device 836 may be utilized in combination with processor 804 to provide graphical representations of aspects of the present disclosure. In addition to a display device, computer system 800 may include one or more other peripheral output devices including, but not limited to, an audio speaker, a printer, and any combinations thereof. Such peripheral output devices may be connected to bus 812 via a peripheral interface 856. Examples of a peripheral interface include, but are not limited to, a serial port, a USB connection, a FIREWIRE connection, a parallel connection, and any combinations thereof.

Now referring to FIG. 9 , an exemplary embodiment 900 of a flight controller 904 is illustrated. As used in this disclosure a “flight controller” is a computing device of a plurality of computing devices dedicated to data storage, security, distribution of traffic for load balancing, and flight instruction. Flight controller 904 may include and/or communicate with any computing device as described in this disclosure, including without limitation a microcontroller, microprocessor, digital signal processor (DSP) and/or system on a chip (SoC) as described in this disclosure. Further, flight controller 904 may include a single computing device operating independently, or may include two or more computing device operating in concert, in parallel, sequentially or the like; two or more computing devices may be included together in a single computing device or in two or more computing devices. In embodiments, flight controller 904 may be installed in an aircraft, may control the aircraft remotely, and/or may include an element installed in the aircraft and a remote element in communication therewith.

In an embodiment, and still referring to FIG. 9 , flight controller 904 may include a signal transformation component 908. As used in this disclosure a “signal transformation component” is a component that transforms and/or converts a first signal to a second signal, wherein a signal may include one or more digital and/or analog signals. For example, and without limitation, signal transformation component 908 may be configured to perform one or more operations such as preprocessing, lexical analysis, parsing, semantic analysis, and the like thereof. In an embodiment, and without limitation, signal transformation component 908 may include one or more analog-to-digital convertors that transform a first signal of an analog signal to a second signal of a digital signal. For example, and without limitation, an analog-to-digital converter may convert an analog input signal to a 10-bit binary digital representation of that signal. In another embodiment, signal transformation component 908 may include transforming one or more low-level languages such as, but not limited to, machine languages and/or assembly languages. For example, and without limitation, signal transformation component 908 may include transforming a binary language signal to an assembly language signal. In an embodiment, and without limitation, signal transformation component 908 may include transforming one or more high-level languages and/or formal languages such as but not limited to alphabets, strings, and/or languages. For example, and without limitation, high-level languages may include one or more system languages, scripting languages, domain-specific languages, visual languages, esoteric languages, and the like thereof. As a further non-limiting example, high-level languages may include one or more algebraic formula languages, business data languages, string and list languages, object-oriented languages, and the like thereof.

Still referring to FIG. 9 , signal transformation component 908 may be configured to optimize an intermediate representation 912. As used in this disclosure an “intermediate representation” is a data structure and/or code that represents the input signal. Signal transformation component 908 may optimize intermediate representation as a function of a data-flow analysis, dependence analysis, alias analysis, pointer analysis, escape analysis, and the like thereof. In an embodiment, and without limitation, signal transformation component 908 may optimize intermediate representation 912 as a function of one or more inline expansions, dead code eliminations, constant propagation, loop transformations, and/or automatic parallelization functions. In another embodiment, signal transformation component 908 may optimize intermediate representation as a function of a machine dependent optimization such as a peephole optimization, wherein a peephole optimization may rewrite short sequences of code into more efficient sequences of code. Signal transformation component 908 may optimize intermediate representation to generate an output language, wherein an “output language,” as used herein, is the native machine language of flight controller 904. For example, and without limitation, native machine language may include one or more binary and/or numerical languages.

In an embodiment, and without limitation, signal transformation component 908 may include transform one or more inputs and outputs as a function of an error correction code. An error correction code, also known as error correcting code (ECC), is an encoding of a message or lot of data using redundant information, permitting recovery of corrupted data. An ECC may include a block code, in which information is encoded on fixed-size packets and/or blocks of data elements such as symbols of predetermined size, bits, or the like. Reed-Solomon coding, in which message symbols within a symbol set having q symbols are encoded as coefficients of a polynomial of degree less than or equal to a natural number k, over a finite field F with q elements; strings so encoded have a minimum hamming distance of k+1, and permit correction of (q−k−1)/2 erroneous symbols. Block code may alternatively or additionally be implemented using Golay coding, also known as binary Golay coding, Bose-Chaudhuri, Hocquenghuem (BCH) coding, multidimensional parity-check coding, and/or Hamming codes. An ECC may alternatively or additionally be based on a convolutional code.

In an embodiment, and still referring to FIG. 9 , flight controller 904 may include a reconfigurable hardware platform 916. A “reconfigurable hardware platform,” as used herein, is a component and/or unit of hardware that may be reprogrammed, such that, for instance, a data path between elements such as logic gates or other digital circuit elements may be modified to change an algorithm, state, logical sequence, or the like of the component and/or unit. This may be accomplished with such flexible high-speed computing fabrics as field-programmable gate arrays (FPGAs), which may include a grid of interconnected logic gates, connections between which may be severed and/or restored to program in modified logic. Reconfigurable hardware platform 916 may be reconfigured to enact any algorithm and/or algorithm selection process received from another computing device and/or created using machine-learning processes.

Still referring to FIG. 9 , reconfigurable hardware platform 916 may include a logic component 920. As used in this disclosure a “logic component” is a component that executes instructions on output language. For example, and without limitation, logic component may perform basic arithmetic, logic, controlling, input/output operations, and the like thereof. Logic component 920 may include any suitable processor, such as without limitation a component incorporating logical circuitry for performing arithmetic and logical operations, such as an arithmetic and logic unit (ALU), which may be regulated with a state machine and directed by operational inputs from memory and/or sensors; logic component 920 may be organized according to Von Neumann and/or Harvard architecture as a non-limiting example. Logic component 920 may include, incorporate, and/or be incorporated in, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), Field Programmable Gate Array (FPGA), Complex Programmable Logic Device (CPLD), Graphical Processing Unit (GPU), general purpose GPU, Tensor Processing Unit (TPU), analog or mixed signal processor, Trusted Platform Module (TPM), a floating point unit (FPU), and/or system on a chip (SoC). In an embodiment, logic component 920 may include one or more integrated circuit microprocessors, which may contain one or more central processing units, central processors, and/or main processors, on a single metal-oxide-semiconductor chip. Logic component 920 may be configured to execute a sequence of stored instructions to be performed on the output language and/or intermediate representation 912. Logic component 920 may be configured to fetch and/or retrieve the instruction from a memory cache, wherein a “memory cache,” as used in this disclosure, is a stored instruction set on flight controller 904. Logic component 920 may be configured to decode the instruction retrieved from the memory cache to opcodes and/or operands. Logic component 920 may be configured to execute the instruction on intermediate representation 912 and/or output language. For example, and without limitation, logic component 920 may be configured to execute an addition operation on intermediate representation 912 and/or output language.

In an embodiment, and without limitation, logic component 920 may be configured to calculate a flight element 924. As used in this disclosure a “flight element” is an element of datum denoting a relative status of aircraft. For example, and without limitation, flight element 924 may denote one or more torques, thrusts, airspeed velocities, forces, altitudes, groundspeed velocities, directions during flight, directions facing, forces, orientations, and the like thereof. For example, and without limitation, flight element 924 may denote that aircraft is cruising at an altitude and/or with a sufficient magnitude of forward thrust. As a further non-limiting example, flight status may denote that is building thrust and/or groundspeed velocity in preparation for a takeoff. As a further non-limiting example, flight element 924 may denote that aircraft is following a flight path accurately and/or sufficiently.

Still referring to FIG. 9 , flight controller 904 may include a chipset component 928. As used in this disclosure a “chipset component” is a component that manages data flow. In an embodiment, and without limitation, chipset component 928 may include a northbridge data flow path, wherein the northbridge dataflow path may manage data flow from logic component 920 to a high-speed device and/or component, such as a RAM, graphics controller, and the like thereof. In another embodiment, and without limitation, chipset component 928 may include a southbridge data flow path, wherein the southbridge dataflow path may manage data flow from logic component 920 to lower-speed peripheral buses, such as a peripheral component interconnect (PCI), industry standard architecture (ICA), and the like thereof. In an embodiment, and without limitation, southbridge data flow path may include managing data flow between peripheral connections such as ethernet, USB, audio devices, and the like thereof. Additionally or alternatively, chipset component 928 may manage data flow between logic component 920, memory cache, and a flight component 932. As used in this disclosure a “flight component” is a portion of an aircraft that can be moved or adjusted to affect one or more flight elements. For example, flight component 932 may include a component used to affect the aircrafts' roll and pitch which may comprise one or more ailerons. As a further example, flight component 932 may include a rudder to control yaw of an aircraft. In an embodiment, chipset component 928 may be configured to communicate with a plurality of flight components as a function of flight element 924. For example, and without limitation, chipset component 928 may transmit to an aircraft rotor to reduce torque of a first lift propulsor and increase the forward thrust produced by a pusher component to perform a flight maneuver.

In an embodiment, and still referring to FIG. 9 , flight controller 904 may be configured generate an autonomous function. As used in this disclosure an “autonomous function” is a mode and/or function of flight controller 904 that controls aircraft automatically. For example, and without limitation, autonomous function may perform one or more aircraft maneuvers, take offs, landings, altitude adjustments, flight leveling adjustments, turns, climbs, and/or descents. As a further non-limiting example, autonomous function may adjust one or more airspeed velocities, thrusts, torques, and/or groundspeed velocities. As a further non-limiting example, autonomous function may perform one or more flight path corrections and/or flight path modifications as a function of flight element 924. In an embodiment, autonomous function may include one or more modes of autonomy such as, but not limited to, autonomous mode, semi-autonomous mode, and/or non-autonomous mode. As used in this disclosure “autonomous mode” is a mode that automatically adjusts and/or controls aircraft and/or the maneuvers of aircraft in its entirety. For example, autonomous mode may denote that flight controller 904 will adjust the aircraft. As used in this disclosure a “semi-autonomous mode” is a mode that automatically adjusts and/or controls a portion and/or section of aircraft. For example, and without limitation, semi-autonomous mode may denote that a pilot will control the propulsors, wherein flight controller 904 will control the ailerons and/or rudders. As used in this disclosure “non-autonomous mode” is a mode that denotes a pilot will control aircraft and/or maneuvers of aircraft in its entirety.

In an embodiment, and still referring to FIG. 9 , flight controller 904 may generate autonomous function as a function of an autonomous machine-learning model. As used in this disclosure an “autonomous machine-learning model” is a machine-learning model to produce an autonomous function output given flight element 924 and a pilot signal 936 as inputs; this is in contrast to a non-machine learning software program where the commands to be executed are determined in advance by a user and written in a programming language. As used in this disclosure a “pilot signal” is an element of datum representing one or more functions a pilot is controlling and/or adjusting. For example, pilot signal 936 may denote that a pilot is controlling and/or maneuvering ailerons, wherein the pilot is not in control of the rudders and/or propulsors. In an embodiment, pilot signal 936 may include an implicit signal and/or an explicit signal. For example, and without limitation, pilot signal 936 may include an explicit signal, wherein the pilot explicitly states there is a lack of control and/or desire for autonomous function. As a further non-limiting example, pilot signal 936 may include an explicit signal directing flight controller 904 to control and/or maintain a portion of aircraft, a portion of the flight plan, the entire aircraft, and/or the entire flight plan. As a further non-limiting example, pilot signal 936 may include an implicit signal, wherein flight controller 904 detects a lack of control such as by a malfunction, torque alteration, flight path deviation, and the like thereof. In an embodiment, and without limitation, pilot signal 936 may include one or more explicit signals to reduce torque, and/or one or more implicit signals that torque may be reduced due to reduction of airspeed velocity. In an embodiment, and without limitation, pilot signal 936 may include one or more local and/or global signals. For example, and without limitation, pilot signal 936 may include a local signal that is transmitted by a pilot and/or crew member. As a further non-limiting example, pilot signal 936 may include a global signal that is transmitted by air traffic control and/or one or more remote users that are in communication with the pilot of aircraft. In an embodiment, pilot signal 936 may be received as a function of a tri-state bus and/or multiplexor that denotes an explicit pilot signal should be transmitted prior to any implicit or global pilot signal.

Still referring to FIG. 9 , autonomous machine-learning model may include one or more autonomous machine-learning processes such as supervised, unsupervised, or reinforcement machine-learning processes that flight controller 904 and/or a remote device may or may not use in the generation of autonomous function. As used in this disclosure “remote device” is an external device to flight controller 904. Additionally or alternatively, autonomous machine-learning model may include one or more autonomous machine-learning processes that a field-programmable gate array (FPGA) may or may not use in the generation of autonomous function. Autonomous machine-learning process may include, without limitation machine learning processes such as simple linear regression, multiple linear regression, polynomial regression, support vector regression, ridge regression, lasso regression, elasticnet regression, decision tree regression, random forest regression, logistic regression, logistic classification, K-nearest neighbors, support vector machines, kernel support vector machines, naïve bayes, decision tree classification, random forest classification, K-means clustering, hierarchical clustering, dimensionality reduction, principal component analysis, linear discriminant analysis, kernel principal component analysis, Q-learning, State Action Reward State Action (SARSA), Deep-Q network, Markov decision processes, Deep Deterministic Policy Gradient (DDPG), or the like thereof.

In an embodiment, and still referring to FIG. 9 , autonomous machine learning model may be trained as a function of autonomous training data, wherein autonomous training data may correlate a flight element, pilot signal, and/or simulation data to an autonomous function. For example, and without limitation, a flight element of an airspeed velocity, a pilot signal of limited and/or no control of propulsors, and a simulation data of required airspeed velocity to reach the destination may result in an autonomous function that includes a semi-autonomous mode to increase thrust of the propulsors. Autonomous training data may be received as a function of user-entered valuations of flight elements, pilot signals, simulation data, and/or autonomous functions. Flight controller 904 may receive autonomous training data by receiving correlations of flight element, pilot signal, and/or simulation data to an autonomous function that were previously received and/or determined during a previous iteration of generation of autonomous function. Autonomous training data may be received by one or more remote devices and/or FPGAs that at least correlate a flight element, pilot signal, and/or simulation data to an autonomous function. Autonomous training data may be received in the form of one or more user-entered correlations of a flight element, pilot signal, and/or simulation data to an autonomous function.

Still referring to FIG. 9 , flight controller 904 may receive autonomous machine-learning model from a remote device and/or FPGA that utilizes one or more autonomous machine learning processes, wherein a remote device and an FPGA is described above in detail. For example, and without limitation, a remote device may include a computing device, external device, processor, FPGA, microprocessor and the like thereof. Remote device and/or FPGA may perform the autonomous machine-learning process using autonomous training data to generate autonomous function and transmit the output to flight controller 904. Remote device and/or FPGA may transmit a signal, bit, datum, or parameter to flight controller 904 that at least relates to autonomous function. Additionally or alternatively, the remote device and/or FPGA may provide an updated machine-learning model. For example, and without limitation, an updated machine-learning model may be comprised of a firmware update, a software update, a autonomous machine-learning process correction, and the like thereof. As a non-limiting example a software update may incorporate a new simulation data that relates to a modified flight element. Additionally or alternatively, the updated machine learning model may be transmitted to the remote device and/or FPGA, wherein the remote device and/or FPGA may replace the autonomous machine-learning model with the updated machine-learning model and generate the autonomous function as a function of the flight element, pilot signal, and/or simulation data using the updated machine-learning model. The updated machine-learning model may be transmitted by the remote device and/or FPGA and received by flight controller 904 as a software update, firmware update, or corrected autonomous machine-learning model. For example, and without limitation autonomous machine learning model may utilize a neural net machine-learning process, wherein the updated machine-learning model may incorporate a gradient boosting machine-learning process.

Still referring to FIG. 9 , flight controller 904 may include, be included in, and/or communicate with a mobile device such as a mobile telephone or smartphone. Further, flight controller may communicate with one or more additional devices as described below in further detail via a network interface device. The network interface device may be utilized for commutatively connecting a flight controller to one or more of a variety of networks, and one or more devices. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, an enterprise network), a local area network (e.g., a network associated with an office, a building, a campus or other relatively small geographic space), a telephone network, a data network associated with a telephone/voice provider (e.g., a mobile communications provider data and/or voice network), a direct connection between two computing devices, and any combinations thereof. The network may include any network topology and can may employ a wired and/or a wireless mode of communication.

In an embodiment, and still referring to FIG. 9 , flight controller 904 may include, but is not limited to, for example, a cluster of flight controllers in a first location and a second flight controller or cluster of flight controllers in a second location. Flight controller 904 may include one or more flight controllers dedicated to data storage, security, distribution of traffic for load balancing, and the like. Flight controller 904 may be configured to distribute one or more computing tasks as described below across a plurality of flight controllers, which may operate in parallel, in series, redundantly, or in any other manner used for distribution of tasks or memory between computing devices. For example, and without limitation, flight controller 904 may implement a control algorithm to distribute and/or command the plurality of flight controllers. As used in this disclosure a “control algorithm” is a finite sequence of well-defined computer implementable instructions that may determine the flight component of the plurality of flight components to be adjusted. For example, and without limitation, control algorithm may include one or more algorithms that reduce and/or prevent aviation asymmetry. As a further non-limiting example, control algorithms may include one or more models generated as a function of a software including, but not limited to Simulink by MathWorks, Natick, Massachusetts, USA. In an embodiment, and without limitation, control algorithm may be configured to generate an auto-code, wherein an “auto-code,” is used herein, is a code and/or algorithm that is generated as a function of the one or more models and/or software's. In another embodiment, control algorithm may be configured to produce a segmented control algorithm. As used in this disclosure a “segmented control algorithm” is control algorithm that has been separated and/or parsed into discrete sections. For example, and without limitation, segmented control algorithm may parse control algorithm into two or more segments, wherein each segment of control algorithm may be performed by one or more flight controllers operating on distinct flight components.

In an embodiment, and still referring to FIG. 9 , control algorithm may be configured to determine a segmentation boundary as a function of segmented control algorithm. As used in this disclosure a “segmentation boundary” is a limit and/or delineation associated with the segments of the segmented control algorithm. For example, and without limitation, segmentation boundary may denote that a segment in the control algorithm has a first starting section and/or a first ending section. As a further non-limiting example, segmentation boundary may include one or more boundaries associated with an ability of flight component 932. In an embodiment, control algorithm may be configured to create an optimized signal communication as a function of segmentation boundary. For example, and without limitation, optimized signal communication may include identifying the discrete timing required to transmit and/or receive the one or more segmentation boundaries. In an embodiment, and without limitation, creating optimized signal communication further comprises separating a plurality of signal codes across the plurality of flight controllers. For example, and without limitation the plurality of flight controllers may include one or more formal networks, wherein formal networks transmit data along an authority chain and/or are limited to task-related communications. As a further non-limiting example, communication network may include informal networks, wherein informal networks transmit data in any direction. In an embodiment, and without limitation, the plurality of flight controllers may include a chain path, wherein a “chain path,” as used herein, is a linear communication path comprising a hierarchy that data may flow through. In an embodiment, and without limitation, the plurality of flight controllers may include an all-channel path, wherein an “all-channel path,” as used herein, is a communication path that is not restricted to a particular direction. For example, and without limitation, data may be transmitted upward, downward, laterally, and the like thereof. In an embodiment, and without limitation, the plurality of flight controllers may include one or more neural networks that assign a weighted value to a transmitted datum. For example, and without limitation, a weighted value may be assigned as a function of one or more signals denoting that a flight component is malfunctioning and/or in a failure state.

Still referring to FIG. 9 , the plurality of flight controllers may include a master bus controller. As used in this disclosure a “master bus controller” is one or more devices and/or components that are connected to a bus to initiate a direct memory access transaction, wherein a bus is one or more terminals in a bus architecture. Master bus controller may communicate using synchronous and/or asynchronous bus control protocols. In an embodiment, master bus controller may include flight controller 904. In another embodiment, master bus controller may include one or more universal asynchronous receiver-transmitters (UART). For example, and without limitation, master bus controller may include one or more bus architectures that allow a bus to initiate a direct memory access transaction from one or more buses in the bus architectures. As a further non-limiting example, master bus controller may include one or more peripheral devices and/or components to communicate with another peripheral device and/or component and/or the master bus controller. In an embodiment, master bus controller may be configured to perform bus arbitration. As used in this disclosure “bus arbitration” is method and/or scheme to prevent multiple buses from attempting to communicate with and/or connect to master bus controller. For example and without limitation, bus arbitration may include one or more schemes such as a small computer interface system, wherein a small computer interface system is a set of standards for physical connecting and transferring data between peripheral devices and master bus controller by defining commands, protocols, electrical, optical, and/or logical interfaces. In an embodiment, master bus controller may receive intermediate representation 912 and/or output language from logic component 920, wherein output language may include one or more analog-to-digital conversions, low bit rate transmissions, message encryptions, digital signals, binary signals, logic signals, analog signals, and the like thereof described above in detail.

Still referring to FIG. 9 , master bus controller may communicate with a slave bus. As used in this disclosure a “slave bus” is one or more peripheral devices and/or components that initiate a bus transfer. For example, and without limitation, slave bus may receive one or more controls and/or asymmetric communications from master bus controller, wherein slave bus transfers data stored to master bus controller. In an embodiment, and without limitation, slave bus may include one or more internal buses, such as but not limited to a/an internal data bus, memory bus, system bus, front-side bus, and the like thereof. In another embodiment, and without limitation, slave bus may include one or more external buses such as external flight controllers, external computers, remote devices, printers, aircraft computer systems, flight control systems, and the like thereof.

In an embodiment, and still referring to FIG. 9 , control algorithm may optimize signal communication as a function of determining one or more discrete timings. For example, and without limitation master bus controller may synchronize timing of the segmented control algorithm by injecting high priority timing signals on a bus of the master bus control. As used in this disclosure a “high priority timing signal” is information denoting that the information is important. For example, and without limitation, high priority timing signal may denote that a section of control algorithm is of high priority and should be analyzed and/or transmitted prior to any other sections being analyzed and/or transmitted. In an embodiment, high priority timing signal may include one or more priority packets. As used in this disclosure a “priority packet” is a formatted unit of data that is communicated between the plurality of flight controllers. For example, and without limitation, priority packet may denote that a section of control algorithm should be used and/or is of greater priority than other sections.

Still referring to FIG. 9 , flight controller 904 may also be implemented using a “shared nothing” architecture in which data is cached at the worker, in an embodiment, this may enable scalability of aircraft and/or computing device. Flight controller 904 may include a distributer flight controller. As used in this disclosure a “distributer flight controller” is a component that adjusts and/or controls a plurality of flight components as a function of a plurality of flight controllers. For example, distributer flight controller may include a flight controller that communicates with a plurality of additional flight controllers and/or clusters of flight controllers. In an embodiment, distributed flight control may include one or more neural networks. For example, neural network also known as an artificial neural network, is a network of “nodes,” or data structures having one or more inputs, one or more outputs, and a function determining outputs based on inputs. Such nodes may be organized in a network, such as without limitation a convolutional neural network, including an input layer of nodes, one or more intermediate layers, and an output layer of nodes. Connections between nodes may be created via the process of “training” the network, in which elements from a training dataset are applied to the input nodes, a suitable training algorithm (such as Levenberg-Marquardt, conjugate gradient, simulated annealing, or other algorithms) is then used to adjust the connections and weights between nodes in adjacent layers of the neural network to produce the desired values at the output nodes. This process is sometimes referred to as deep learning.

Still referring to FIG. 9 , a node may include, without limitation a plurality of inputs x_(i) that may receive numerical values from inputs to a neural network containing the node and/or from other nodes. Node may perform a weighted sum of inputs using weights w_(i) that are multiplied by respective inputs x_(i). Additionally or alternatively, a bias b may be added to the weighted sum of the inputs such that an offset is added to each unit in the neural network layer that is independent of the input to the layer. The weighted sum may then be input into a function φ, which may generate one or more outputs y. Weight w_(i) applied to an input x_(i) may indicate whether the input is “excitatory,” indicating that it has strong influence on the one or more outputs y, for instance by the corresponding weight having a large numerical value, and/or a “inhibitory,” indicating it has a weak effect influence on the one more inputs y, for instance by the corresponding weight having a small numerical value. The values of weights w_(i) may be determined by training a neural network using training data, which may be performed using any suitable process as described above. In an embodiment, and without limitation, a neural network may receive semantic units as inputs and output vectors representing such semantic units according to weights w_(i) that are derived using machine-learning processes as described in this disclosure.

Still referring to FIG. 9 , flight controller may include a sub-controller 940. As used in this disclosure a “sub-controller” is a controller and/or component that is part of a distributed controller as described above; for instance, flight controller 904 may be and/or include a distributed flight controller made up of one or more sub-controllers. For example, and without limitation, sub-controller 940 may include any controllers and/or components thereof that are similar to distributed flight controller and/or flight controller as described above. Sub-controller 940 may include any component of any flight controller as described above. Sub-controller 940 may be implemented in any manner suitable for implementation of a flight controller as described above. As a further non-limiting example, sub-controller 940 may include one or more processors, logic components and/or computing devices capable of receiving, processing, and/or transmitting data across the distributed flight controller as described above. As a further non-limiting example, sub-controller 940 may include a controller that receives a signal from a first flight controller and/or first distributed flight controller component and transmits the signal to a plurality of additional sub-controllers and/or flight components.

Still referring to FIG. 9 , flight controller may include a co-controller 944. As used in this disclosure a “co-controller” is a controller and/or component that joins flight controller 904 as components and/or nodes of a distributer flight controller as described above. For example, and without limitation, co-controller 944 may include one or more controllers and/or components that are similar to flight controller 904. As a further non-limiting example, co-controller 944 may include any controller and/or component that joins flight controller 904 to distributer flight controller. As a further non-limiting example, co-controller 944 may include one or more processors, logic components and/or computing devices capable of receiving, processing, and/or transmitting data to and/or from flight controller 904 to distributed flight control system. Co-controller 944 may include any component of any flight controller as described above. Co-controller 944 may be implemented in any manner suitable for implementation of a flight controller as described above.

In an embodiment, and with continued reference to FIG. 9 , flight controller 904 may be designed and/or configured to perform any method, method step, or sequence of method steps in any embodiment described in this disclosure, in any order and with any degree of repetition. For instance, flight controller 904 may be configured to perform a single step or sequence repeatedly until a desired or commanded outcome is achieved; repetition of a step or a sequence of steps may be performed iteratively and/or recursively using outputs of previous repetitions as inputs to subsequent repetitions, aggregating inputs and/or outputs of repetitions to produce an aggregate result, reduction or decrement of one or more variables such as global variables, and/or division of a larger processing task into a set of iteratively addressed smaller processing tasks. Flight controller may perform any step or sequence of steps as described in this disclosure in parallel, such as simultaneously and/or substantially simultaneously performing a step two or more times using two or more parallel threads, processor cores, or the like; division of tasks between parallel threads and/or processes may be performed according to any protocol suitable for division of tasks between iterations. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various ways in which steps, sequences of steps, processing tasks, and/or data may be subdivided, shared, or otherwise dealt with using iteration, recursion, and/or parallel processing.

The foregoing has been a detailed description of illustrative embodiments of the invention. Various modifications and additions can be made without departing from the spirit and scope of this invention. Features of each of the various embodiments described above may be combined with features of other described embodiments as appropriate in order to provide a multiplicity of feature combinations in associated new embodiments. Furthermore, while the foregoing describes a number of separate embodiments, what has been described herein is merely illustrative of the application of the principles of the present invention. Additionally, although particular methods herein may be illustrated and/or described as being performed in a specific order, the ordering is highly variable within ordinary skill to achieve methods, systems, and software according to the present disclosure. Accordingly, this description is meant to be taken only by way of example, and not to otherwise limit the scope of this invention.

Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various changes, omissions and additions may be made to that which is specifically disclosed herein without departing from the spirit and scope of the present invention. 

What is claimed is:
 1. A system for dynamic excitation of an energy storage element configured for use in an electric aircraft, the system comprising: a plurality of propulsors mechanically connected to the electric aircraft; a plurality of energy storage elements electrically connected to the plurality of propulsors; a bus element, wherein the bus element is electrically connected to the plurality of energy storage elements; and a cross tie element, the cross tie element connected to the bus element and configured to disconnect a first energy storage element of the plurality of storage elements from a second energy storage element of the plurality of storage elements, wherein the first storage element is electrically connected to a first propulsor element incorporated in the plurality of propulsors and the second energy storage element is electrically connected to a second propulsor element incorporated in the plurality of propulsors.
 2. The system of claim 1, wherein the cross tie element comprises at least a switch.
 3. The system of claim 1, wherein the plurality of energy storage elements comprises a battery module.
 4. The system of claim 1, further comprising a modulator unit electrically connected to the bus element, the modulator unit configured to modulate a first electrical command to the first propulsor element and a second electrical command to the second propulsor element.
 5. The system of claim 4, wherein modulating the first electrical command and second electrical command comprises drawing electrical energy from the first energy storage element.
 6. The system of claim 4, wherein the modulator unit is further configured to measure at least an electrical parameter as a function of the modulation of the first electrical command.
 7. The system of claim 6, wherein measuring the electrical parameter further comprises detecting a change in the electrical parameter.
 8. The system of claim 1, wherein the bus element comprises a ring bus.
 9. The system of claim 1, wherein the cross tie element is configured to: receive a datum from at least a sensor; and disconnect the first energy storage element from the second energy storage element as a function of the datum.
 10. The system of claim 9, wherein the energy datum comprises a health datum.
 11. A method for dynamic excitation of an energy storage element configured for use in electric aircraft, the method comprising: disconnecting, by a cross tie element connected to a bus element, a first energy storage element electrically connected to the bus element from a second energy storage element electrically connected to the bus element, wherein the first storage element is electrically connected to a first propulsor element incorporated in a plurality of propulsors and the second energy storage element is electrically connected to a second propulsor element incorporated in the plurality of propulsors.
 12. The method of claim 11, wherein cross tie element comprises a switch.
 13. The method of claim 11, wherein the energy storage element comprises a battery module.
 14. The method of claim 11, wherein the modulator unit comprises a processor.
 15. The method of claim 14, wherein modulating the first electrical command and second electrical command comprises drawing electrical energy from the first energy storage element.
 16. The method of claim 15, wherein measuring the electrical parameter further comprises detecting a change in the electrical parameter.
 17. The method of claim 14, wherein the modulator unit is further configured to measure at least an electrical parameter as a function of the modulation of the first electrical command.
 18. The method of claim 11, further comprising modulating, by a modulator unit, a first electrical command to the first propulsor element and a second electrical command to the second propulsor element.
 19. The method of claim 11, wherein the cross tie element is configured to: receive a datum from at least a sensor; and disconnect the first energy storage element from the second energy storage element as a function of the datum.
 20. The method of claim 19, wherein the energy datum comprises a health datum. 